CN114199503A - Test model for testing anti-icing and deicing effects of super-hydrophobic material - Google Patents
Test model for testing anti-icing and deicing effects of super-hydrophobic material Download PDFInfo
- Publication number
- CN114199503A CN114199503A CN202111588748.4A CN202111588748A CN114199503A CN 114199503 A CN114199503 A CN 114199503A CN 202111588748 A CN202111588748 A CN 202111588748A CN 114199503 A CN114199503 A CN 114199503A
- Authority
- CN
- China
- Prior art keywords
- main body
- model
- icing
- model main
- testing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 61
- 230000003075 superhydrophobic effect Effects 0.000 title claims abstract description 45
- 239000000463 material Substances 0.000 title claims abstract description 34
- 230000000694 effects Effects 0.000 title claims abstract description 27
- 238000010438 heat treatment Methods 0.000 claims abstract description 26
- 238000009413 insulation Methods 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
Images
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
- G01M9/08—Aerodynamic models
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the field of wind tunnel testing, and discloses a test model for testing anti-icing and deicing effects of a super-hydrophobic material, which comprises a model main body, wherein a rear end cover plate is arranged at the bottom of the model main body, and the model main body is connected with a front edge skin; the shape of the model main body, the rear end cover plate and the front edge skin after being connected is the same as that of the wing; the inner surface of the front edge skin is provided with a heating film, the inner side of the front edge skin is provided with a blind hole along the chord length direction, and a thermocouple is installed in the blind hole; and a super-hydrophobic skin is arranged on the outer surface of the front edge skin. The invention effectively solves the problem of testing the anti-icing and deicing effects of the super-hydrophobic material in an icing wind tunnel.
Description
Technical Field
The invention belongs to the field of wind tunnel tests, and particularly relates to a test model for testing anti-icing and deicing effects of a super-hydrophobic material.
Background
The icing phenomenon of the aircraft wings generates huge hidden danger to safe flight of the aircraft wings, and corresponding icing wind tunnel tests are needed for verifying the effect of the aircraft wing anti-icing and deicing technology and quantitatively analyzing the influence of icing on the aerodynamic performance of the aircraft. The icing wind tunnel test is a common method for researching the icing mechanism of the wings of the airplane and is an important means for obtaining the icing state. The contact angle of water drops on the surface of the super-hydrophobic material is larger, the water drops on the surface are easy to fall off, and the super-hydrophobic material has a better application prospect in the field of aircraft deicing and ice prevention. Before being applied to an anti-icing and deicing system of a real airplane, the super-hydrophobic material needs to be subjected to corresponding icing test tests in an icing wind tunnel to determine the anti-icing and deicing effects of the super-hydrophobic material. At present, the testing of the anti-icing and deicing effects of the super-hydrophobic material cannot be completed in an icing wind tunnel under different temperature conditions, and the comparison test of the super-hydrophobic material and a common material cannot be completed at one time.
Disclosure of Invention
In order to solve the problem that the prior art cannot test the anti-icing and deicing effects of the super-hydrophobic material under different temperature conditions in an icing wind tunnel, the invention provides a test model for testing the anti-icing and deicing effects of the super-hydrophobic material.
The invention adopts the specific scheme that: a test model for testing the anti-icing and deicing effects of a super-hydrophobic material comprises a model main body, wherein a rear end cover plate is arranged at the bottom of the model main body, and the model main body is connected with a front edge skin; the shape of the model main body, the rear end cover plate and the front edge skin after being connected is the same as that of the wing; the inner surface of the front edge skin is provided with a heating film, the inner side of the front edge skin is provided with a blind hole along the chord length direction, and a thermocouple is installed in the blind hole; and a super-hydrophobic skin is arranged on the outer surface of the front edge skin.
And the heat insulation pad is arranged between the front edge skin and the model main body.
The model main body and the front edge skin are positioned through mortise and tenon type rabbets and are connected with the model main body through countersunk head screws arranged on two sides of the model main body.
The two ends of the model main body are respectively provided with a driving shaft and a driven shaft, the driving shaft and the driven shaft are hollow shafts, and power lines of the heating film and the thermocouple are arranged inside the driving shaft and the driven shaft.
During testing, the model driving shaft and the model driven shaft are installed on the horizontal half-mold supporting mechanism of the testing section.
The model comprises a model body and is characterized in that a rear end cover plate is arranged at the bottom of the model body, a limiting block is arranged on the rear end cover plate, a limiting groove matched with the limiting block is arranged at the bottom of the model body, and the limiting block is matched with the limiting groove to complete connection of the model body and the limiting block.
The rear end cover plate is connected with the model main body through the stop blocks arranged on two sides of the model main body.
And one side of the outer surface of the front edge skin is provided with a super-hydrophobic skin, and the other side of the outer surface of the front edge skin is provided with a conventional skin.
Compared with the prior art, the invention has the following beneficial effects:
1. the shape of the model main body, the rear end cover plate and the front edge skin after connection is the same as that of the wing, the front edge skin is of a detachable structure, the heating film is arranged on the inner surface of the front edge skin and used for heating the surface of the skin, and then the super-hydrophobic skin arranged on the front edge skin is heated, so that the observation of the anti-icing and deicing effects of the super-hydrophobic skin at different temperatures is realized.
2. According to the invention, the super-hydrophobic skin and the conventional skin are arranged on the outer surface of the front edge skin, so that the test on the super-hydrophobic skin is completed, and the problem that the anti-icing and deicing test comparison test of the super-hydrophobic material and the common material cannot be completed at one time is solved.
3. According to the invention, by utilizing the tenon-and-mortise structure and the limiting groove, the mode of arranging the handle nail on the side surface of the model main body is adopted, so that the condition that the surface of the ice model uses a connecting piece such as a screw for influencing the icing characteristic is avoided, and after the front edge skin is connected with the model main body, a closed air cavity is formed between the front edge skin and the model main body, so that the heat can be effectively insulated, the ineffective loss of the heat of the heating film is avoided, the test precision is ensured, and the energy loss is avoided.
Drawings
FIG. 1 is a schematic view of the apparatus of the present invention;
FIG. 2 is a schematic sectional view A-A of FIG. 1;
FIG. 3 is a side view of FIG. 1;
fig. 4 is an enlarged view of a portion of fig. 2.
FIG. 5 is a perspective view of a mold body according to the present invention;
FIG. 6 is a perspective view of the leading edge skin of the present invention;
fig. 7 is a perspective view of the device of the present invention.
Wherein the reference numerals are respectively:
1. a model body; 2. a driven shaft; 3. a leading edge skin; 4. a superhydrophobic skin; 5. conventional skin covering; 6. a drive shaft; 7. a rear end cover plate; 8. a heat insulating pad; 9. heating the film; 10. a thermocouple; 11. a stopper; 12. countersunk head screw.
Detailed Description
The present invention will be described in further detail below with reference to the attached drawings, and it should be clearly understood herein that the described embodiments are not all embodiments, but are merely illustrative and not restrictive of the present invention.
A test model for testing the anti-icing and deicing effects of a super-hydrophobic material comprises a model main body 1, wherein a rear end cover plate 7 is arranged at the bottom of the model main body 1, and the model main body 1 is connected with a front edge skin 3; the shape of the model main body 1, the rear end cover plate 7 and the front edge skin 3 after connection is the same as that of a wing; the inner surface of the front edge skin 3 is provided with a heating film 9, the inner side of the front edge skin 3 is provided with a blind hole along the chord length direction, and a thermocouple 10 is installed in the blind hole; the outer surface of the leading edge skin 3 is provided with a super-hydrophobic skin 4. And a heat insulation pad 8 is arranged between the front edge skin 3 and the model main body 1. The provision of the heat insulating mat 8 can reduce the heat transfer of the heating film 9 to the model body 1 through the leading edge skin 3. The thermocouple is arranged for monitoring the surface temperature of the leading edge skin 3 and controlling the heating power of the heating film 9 accordingly; the heating film 9 is provided with a through hole corresponding to the thermocouple wire, and the low-energy-consumption anti-icing and deicing data of the super-hydrophobic material at different temperatures can be acquired by adjusting the power of the heating film.
The super-hydrophobic skin is a skin prepared by adopting a super-hydrophobic material; the conventional skin is prepared from a conventional aluminum alloy material.
And a super-hydrophobic skin is arranged on one side of the outer surface of the front edge skin, a conventional skin is arranged on the other side of the outer surface of the front edge skin, and the anti-icing and deicing effects of the super-hydrophobic skin 4 and the conventional aluminum alloy skin 5 are observed and compared under the same heating power during an icing wind tunnel test.
The model main body 1 and the front edge skin 3 are positioned through mortise and tenon type rabbets and are connected with the model main body 1 through countersunk head screws arranged on two sides of the model main body 1. The two ends of the model main body 1 are respectively provided with a driving shaft 6 and a driven shaft 2, the driving shaft 6 and the driven shaft 2 are hollow shafts, and power lines of the heating film 9 and the thermocouple 10 are arranged inside the driving shaft and the driven shaft. During testing, the driving shaft 6 and the driven shaft 2 are installed on the horizontal half-mold supporting mechanism of the testing section. The model comprises a model body 1 and is characterized in that a rear end cover plate 7 is arranged at the bottom of the model body 1, a limiting block is arranged on the rear end cover plate 7, a limiting groove matched with the limiting block is arranged at the bottom of the model body 1, and the limiting block is matched with the limiting groove to complete connection of the model body 1 and the limiting block. The rear end cover plate 7 is combined with the model main body 1 through the stop blocks 11 arranged on the two sides of the model main body 1. The stopper 11 prevents the rear end cover 7 from moving in the mold extending direction.
The inner part of the model main body is hollow, through holes which are convenient for the driving shaft and the driven shaft to pass through are formed in the two sides of the model main body, and the model main body is provided with a limiting groove which is connected with a limiting block. The model main part sets up the baffle with leading edge covering junction, set up the through-hole that the power cord of being convenient for passes through on the baffle. The shape of the model main body, the rear end cover plate and the front edge skin after being connected is the same as that of the wing, and an inner closed space is formed. A closed air heat insulation layer is formed between the rear side of the heating film and the model main body, and the heat loss of the heating film is reduced by utilizing the excellent heat insulation effect of air.
The invention adopts the structural form of a model main body and a skin, the front edge skin is of a detachable structure, and the front edge skin is connected with a non-test area on the side surface of a connecting screw of the model main body, so that the influence of the surface screw of the skin on the icing state during the icing wind tunnel test is avoided. The heating film is pasted to leading edge covering inboard, and the back is accomplished in the installation of leading edge covering, forms confined air cavity between heating film rear side and model main part, utilizes the good thermal-insulated effect of air, has effectively reduced the calorific loss of heating film. A heat insulation pad is arranged between the front edge skin and the model main body and is used for reducing the heat of the heating film from being transferred from the front edge skin to the rear side model main body; and a thermocouple mounting hole is formed in the front edge skin and used for monitoring the surface temperature of the front edge skin and controlling the heating power of the heating film. During wind tunnel test, the model main body is connected with the wind tunnel test section half-mode mechanism through the driving shaft and the driven shaft, the conventional metal skin with the same thickness and the super-hydrophobic material is pasted on the outer surface of the front edge skin, and the low-energy-consumption anti-icing effect of the super-hydrophobic material under the same wind tunnel test environment with different attack angles, water content and the like can be observed in the modes of a video observation system and the like during the ice wind tunnel test.
The invention provides a test model for testing the anti-icing and deicing effects of a super-hydrophobic material under different temperature conditions, and can complete a comparison test of the super-hydrophobic material and a common material at one time.
The drawings and the explanation are only for one embodiment of the present invention, but the specific protection scope of the present invention is not limited to the above explanation, and any simple replacement or change within the technical idea of the present invention and the technical solution according to the present invention should be within the protection scope of the present invention.
Claims (9)
1. A test model for testing the anti-icing and deicing effects of a super-hydrophobic material is characterized by comprising a model main body (1), wherein a rear end cover plate (7) is arranged at the bottom of the model main body (1), and the model main body (1) is connected with a front edge skin (3); the shape of the model main body (1), the shape of the rear end cover plate (7) and the shape of the front edge skin (3) after connection are the same as the shape of the wing; a heating film (9) is arranged on the inner surface of the front edge skin (3), a blind hole is formed in the inner side of the front edge skin (3) along the chord length direction, and a thermocouple (10) is installed in the blind hole; and the outer surface of the front edge skin (3) is provided with a super-hydrophobic skin (4).
2. Test model for testing the anti-icing and deicing effects of superhydrophobic materials according to claim 1, characterized by a thermal insulation pad (8) arranged between the leading edge skin (3) and the model body (1).
3. The test model for testing the anti-icing and deicing effects of the superhydrophobic material is characterized in that the model main body (1) and the leading edge skin (3) are positioned through mortise and tenon type rabbets and are connected with the model main body (1) through countersunk head screws (12) arranged on two sides of the model main body (1).
4. The test model for testing the anti-icing and deicing effects of the superhydrophobic material according to claim 1, wherein a driving shaft (6) and a driven shaft (2) are respectively arranged at two ends of the model main body (1), the driving shaft (6) and the driven shaft (2) are hollow shafts, and a power line of the heating film (9) and a power line of the thermocouple (10) are wired inside the driving shaft (6) and the driven shaft (2).
5. The test model for testing the anti-icing and deicing effects of the superhydrophobic material according to claim 1, wherein the driving shaft (6) and the driven shaft (2) are mounted on a horizontal half-mold supporting mechanism of a test section during testing.
6. The experimental model for testing the anti-icing and deicing effects of the superhydrophobic material according to claim 1, wherein a sealed air insulation layer is formed between the rear side of the heating film (9) and the model body (1).
7. The test model for testing the anti-icing and deicing effects of the superhydrophobic material according to claim 1, wherein a rear end cover plate (7) is arranged at the bottom of the model main body (1), a limiting block is arranged on the rear end cover plate (7), a limiting groove matched with the limiting block is arranged at the bottom of the model main body (1), and the limiting block is matched with the limiting groove to complete connection of the model main body (1) and the limiting block.
8. The test model for testing the anti-icing and deicing effects of the superhydrophobic material according to claim 7, wherein the back end cover plate (7) is connected with the model main body (1) through stoppers arranged at two sides of the model main body (1).
9. Test model for testing the anti-icing and deicing effects of superhydrophobic materials according to any one of claims 1-8, characterized in that one side of the outer surface of the leading edge skin (3) is provided with a superhydrophobic skin (4) and the other side is provided with a conventional skin (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111588748.4A CN114199503A (en) | 2021-12-23 | 2021-12-23 | Test model for testing anti-icing and deicing effects of super-hydrophobic material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111588748.4A CN114199503A (en) | 2021-12-23 | 2021-12-23 | Test model for testing anti-icing and deicing effects of super-hydrophobic material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114199503A true CN114199503A (en) | 2022-03-18 |
Family
ID=80656161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111588748.4A Pending CN114199503A (en) | 2021-12-23 | 2021-12-23 | Test model for testing anti-icing and deicing effects of super-hydrophobic material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114199503A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115384780A (en) * | 2022-09-02 | 2022-11-25 | 中航通飞华南飞机工业有限公司 | Skin temperature measurement structure and manufacturing method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197941A (en) * | 2015-05-07 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of icing mnncl tcst wing model for aircraft certification checking |
| CN106243952A (en) * | 2015-06-15 | 2016-12-21 | 富士重工业株式会社 | Compo, the wing and anti-deicing system |
| CN106644360A (en) * | 2016-12-08 | 2017-05-10 | 西北工业大学 | Test piece clamping device for ice wind tunnel environmental test chamber |
| CN109696290A (en) * | 2019-02-18 | 2019-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system |
| CN111268142A (en) * | 2020-03-16 | 2020-06-12 | 中国电子科技集团公司第三十八研究所 | Anti-icing structure of unmanned aerial vehicle wing |
| US20210107687A1 (en) * | 2019-10-11 | 2021-04-15 | Dalian University Of Technology | Pressure measuring device for a scale model for elastic similar structure of a wing in a large transport plane |
-
2021
- 2021-12-23 CN CN202111588748.4A patent/CN114199503A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197941A (en) * | 2015-05-07 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of icing mnncl tcst wing model for aircraft certification checking |
| CN106243952A (en) * | 2015-06-15 | 2016-12-21 | 富士重工业株式会社 | Compo, the wing and anti-deicing system |
| CN106644360A (en) * | 2016-12-08 | 2017-05-10 | 西北工业大学 | Test piece clamping device for ice wind tunnel environmental test chamber |
| CN109696290A (en) * | 2019-02-18 | 2019-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system |
| US20210107687A1 (en) * | 2019-10-11 | 2021-04-15 | Dalian University Of Technology | Pressure measuring device for a scale model for elastic similar structure of a wing in a large transport plane |
| CN111268142A (en) * | 2020-03-16 | 2020-06-12 | 中国电子科技集团公司第三十八研究所 | Anti-icing structure of unmanned aerial vehicle wing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115384780A (en) * | 2022-09-02 | 2022-11-25 | 中航通飞华南飞机工业有限公司 | Skin temperature measurement structure and manufacturing method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11009437B2 (en) | Ice test devices | |
| WO2014173043A1 (en) | Carbon crystal anti-icing method and wind driven generator anti-icing system employing same | |
| CN114199503A (en) | Test model for testing anti-icing and deicing effects of super-hydrophobic material | |
| CN202557799U (en) | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device | |
| CN206960261U (en) | Shear strength measurement apparatus between the ice sheet and solid material of a kind of freezing process | |
| CN106240798B (en) | A kind of spar/energy-storage battery integral structure | |
| CN205265933U (en) | Multilayer structure's anti -icing component of electrical heating | |
| CN111284679B (en) | Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio cell cube | |
| CN208134635U (en) | A kind of anti-deicing system for medium-and-large-sized fixed-wing unmanned plane | |
| CN102431650A (en) | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device | |
| Shu et al. | Numerical and experimental investigation of threshold de-icing heat flux of wind turbine | |
| CN110510102A (en) | A kind of sticking type is from hindering heating/super-hydrophobic integral gradient thin-film material | |
| CN109211777A (en) | A kind of experimental provision for the test of wing icing adhesion strength | |
| CN115450865A (en) | Anti-icing system for blades of wind turbine generator | |
| CN211919037U (en) | Icing wind tunnel test device for aircraft anti-icing and deicing leading-edge slat | |
| AU2011325254B2 (en) | Rotor blade with heating device for a wind turbine | |
| CN107117318B (en) | A kind of preparation method of anti-/ deicing composite material functional unit | |
| CN112665843A (en) | Environmental test equipment for airborne atmospheric data probe | |
| Gao et al. | An experimental investigation on an electric-thermal strategy for wind turbines icing mitigation | |
| CN207703982U (en) | A kind of circuit board detection device | |
| CN111731485B (en) | Autonomous intermittent deicing device and installation method and deicing method thereof | |
| CN104727945A (en) | De-icing system of aircraft engine inlet | |
| Strehlow et al. | Capitalizing on the increased flexibility that comes from high power density electrothermal deicing | |
| CN113044237A (en) | Wing flutter model | |
| CN112722286A (en) | Electric heating hydrophobic anti-icing device and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |