CN109211777A - A kind of experimental provision for the test of wing icing adhesion strength - Google Patents
A kind of experimental provision for the test of wing icing adhesion strength Download PDFInfo
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- CN109211777A CN109211777A CN201710540172.1A CN201710540172A CN109211777A CN 109211777 A CN109211777 A CN 109211777A CN 201710540172 A CN201710540172 A CN 201710540172A CN 109211777 A CN109211777 A CN 109211777A
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- wing
- adhesion strength
- icing
- angle
- test
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N19/00—Investigating materials by mechanical methods
- G01N19/04—Measuring adhesive force between materials, e.g. of sealing tape, of coating
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- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention provides a kind of experimental provision for the test of wing icing adhesion strength, and component includes: experimental section cabinet, slide bar, force snesor, bracket, lead screw, handwheel, angle of attack adjustment disk, wing segment, wing fixed disk and wing fixing axle；Wherein fitting machine wing panel part in experimental section cabinet drives experimental section cabinet to move along slide bar by handwheel and lead screw；The wing angle of attack can be adjusted in angle of attack adjustment disk, and ice-formation condition can be adjusted by testing the icing tunnel that box bracket is connected and fixed；After the present apparatus is by the way that wing segment freezes in icing tunnel, the mobile experimental section cabinet of manual loading, the force sensor measuring experimental box body by demarcating in advance acquires aerofoil surface icing adhesion strength to the changing value of poppet pressure.The features such as present invention has installation simple and flexible, can be used for aircraft and the test of helicopter wing icing adhesion strength, can satisfy the different structure wing needs that icing adhesion strength measures under different ice-formation conditions.
Description
Technical field
The present invention relates to a kind of experimental provisions for the test of wing icing adhesion strength, belong to aircraft security technology neck
Domain.
Background technique
Aircraft in the cloud layer containing super-cooling waterdrop when flight, wing, empennage leading edge, propeller, lifting airscrew blade,
The windward sides such as engine intake, pitot, windshield are likely to freeze.Accumulated ice jelly is adhered in the leading edge of a wing, can be drawn
Playing maximum lift coefficient reduces, and stall angle shifts to an earlier date, and increases the resistance of aircraft, lift resistance ratio decline；Have experiments have shown that, work as machine
When nose of wing has the accumulated ice of 1.3cm, airplane ascensional force reduces 50%, and resistance increases by 50%.Therefore, outstanding to the research of the anti-deicing of wing
It is important.
It is available more true using anti-deicing research is carried out in icing tunnel due to the continuous development and improvement of icing tunnel
Real reliable experimental data, and it is able to verify that anti-/ deicing theoretical research.Existing icing adhesion strength research data, which is shown so far, not to be had
Icing adhesion strength is theoretical to be clearly stated, the measurement to icing adhesion strength also due to disunity and there are disagreements.Based on to wing
The requirement of surface icing adhesion strength research, the present invention devise a kind of experimental provision for the test of wing icing adhesion strength, should
Device can be applied in icing tunnel, and change the angle of attack and carry out icing experiment.
Summary of the invention
The invention patent is frozen viscous mainly for the deficiency of the existing adherency force test method that freezes using whole wing surface
The mode of attached power measurement, reaches and provides whole wing icing adhesion strength experimental data, the mesh of support study dies icing adhesion strength theory
's.The features such as present invention has installation simple and flexible, can be used for aircraft and the test of helicopter wing icing adhesion strength, can satisfy
The wing needs that icing adhesion strength measures under different ice-formation conditions.
The technical solution adopted by the present invention is that: a kind of experimental provision for the test of wing icing adhesion strength is provided, it is special
Sign is: solid including experimental section cabinet, slide bar, force snesor, bracket, lead screw, handwheel, angle of attack adjustment disk, wing segment, wing
Price fixing and wing fixing axle；Wherein fitting machine wing panel part in experimental section cabinet drives experimental section cabinet edge by handwheel and lead screw
Slide bar movement；The wing angle of attack can be adjusted in angle of attack adjustment disk, the ice that ice-formation condition can be connected and fixed by testing box bracket
Wind-tunnel is adjusted.
The angle of attack adjustment disk can arbitrarily adjust the wing angle of attack and carry out icing adhesion strength measurement.
The flapping wings type wing can realize the VTOL function of flapping-wing aircraft.
The experimental provision can measure whole section of wing icing adhesion strength.
The experimental provision uses pressure jump value Wings knot between force sensor measuring experimental section cabinet and bracket
Ice adhesion.
The beneficial effects of the present invention are:
1. the adjustable wing attack angle measurement icing adhesion strength of the present invention；
2. the present invention can measure whole section of wing icing adhesion strength；
3. the present invention carries out Wings icing adhesion strength using force sensor measuring pressure jump value；
4. the present invention has installation simple and flexible, it can be used for the various icing adhesion strength tests such as aircraft and helicopter wing
Deng.
Detailed description of the invention
Fig. 1 is experimental provision general structure schematic diagram of the present invention.
Fig. 2 is wing segment schematic diagram.
Fig. 3 is wing fixed disk schematic diagram.
Fig. 4 is wing fixing axle schematic diagram.
Fig. 5 is experimental section cabinet schematic diagram.
Fig. 6 is support schematic diagram.
In figure:
1. 7. angle of attack adjustment disk of handwheel 2. lead screw, 3. experimental section cabinet, 4. force snesor, 5. slide bar, 6. bracket, 8. machine
9. wing fixed disk of wing panel part, 10. wing fixes 11. wing fixing axle of shaft mounting hole
Specific embodiment
Invention is further explained with reference to the accompanying drawing.
As shown in Figure 1, icing adhesion strength experimental provision is mounted in icing tunnel by bracket 6, with icing tunnel closed circuit
Connection can be attached by experimental section cabinet 3, first turn on icing tunnel, change ice-formation condition, be changed by angle of attack adjustment disk 7
Angle of attack when wing segment 8 freezes, freezes in freezing time；It completes after freezing, by the way that handwheel 1, rotation is manually operated
Lead screw 2 drive experimental section cabinet 3 moved along 5 direction of slide bar, between experimental section cabinet 3 and bracket 6 by force snesor 4 into
Row measurement pressure, when aerofoil surface accumulated ice is completely fallen off, the surveyed numerical value of force snesor 4 mutates, by maximum value F0Mutation
At F1, icing adhesion strength numerical value is solved by icing adhesion strength calculation formula:
Fice=F1-F0
As shown in Fig. 2-Fig. 6, wing segment 8 is by installing wing fixing axle 11 inside the fixed shaft mounting hole 10 of wing.Machine
Wing fixing axle 11 connects wing segment 8 using spline form, while being fixed with bolts close to handwheel end, and right side uses axis
Shoulder is fixed；Wing segment 8 uses two wing fixed disks 9 installed in the same direction in the installation of experimental section cabinet 3, is adjusting the angle of attack and is pacifying
After installing wing fixed disk 9, fastened in connection handwheel end installation bolt.Wing fixing axle 11 is at connecting bracket 6 in figure
It is all made of ball bearing, is not indicated in Figure of description.
Claims (4)
1. the present invention provides a kind of experimental provision for the test of wing icing adhesion strength, it is characterised in that: including experimental section case
Body, slide bar, force snesor, bracket, lead screw, handwheel, angle of attack adjustment disk, wing segment, wing fixed disk and wing fixing axle；Its
Fitting machine wing panel part in middle experimental section cabinet drives experimental section cabinet to move along slide bar by handwheel and lead screw；Angle of attack adjustment disk
The wing angle of attack can be adjusted, ice-formation condition can be adjusted by testing the icing tunnel that box bracket is connected and fixed.
2. a kind of experimental provision for the test of wing icing adhesion strength according to claim 1, it is characterised in that: described
Angle of attack adjustment disk can arbitrarily adjust the wing angle of attack and carry out icing adhesion strength measurement.
3. a kind of experimental provision for the test of wing icing adhesion strength according to claim 1, it is characterised in that: described
Experimental provision can measure the icing adhesion strength of whole section of uniform wing.
4. a kind of experimental provision for the test of wing icing adhesion strength according to claim 1, it is characterised in that: described
Experimental provision uses pressure jump value Wings icing adhesion strength between force sensor measuring experimental section cabinet and bracket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710540172.1A CN109211777A (en) | 2017-07-05 | 2017-07-05 | A kind of experimental provision for the test of wing icing adhesion strength |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710540172.1A CN109211777A (en) | 2017-07-05 | 2017-07-05 | A kind of experimental provision for the test of wing icing adhesion strength |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109211777A true CN109211777A (en) | 2019-01-15 |
Family
ID=64992002
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710540172.1A Pending CN109211777A (en) | 2017-07-05 | 2017-07-05 | A kind of experimental provision for the test of wing icing adhesion strength |
Country Status (1)
| Country | Link |
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| CN (1) | CN109211777A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110887748A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Ice collection unit, device and device for measuring shear strength between ice layer and fixed wall |
| CN111076888A (en) * | 2020-01-10 | 2020-04-28 | 北京航空航天大学 | Small vertical backflow ice wind tunnel experimental device for measuring ice accretion adhesion |
| CN111398167A (en) * | 2020-04-24 | 2020-07-10 | 山东大学 | Surface ice adhesion wireless measurement device and method |
| CN113484235A (en) * | 2021-06-25 | 2021-10-08 | 东北农业大学 | Device for measuring ice adhesion strength on surface of wind turbine blade |
| CN115628876A (en) * | 2022-12-08 | 2023-01-20 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN116164928A (en) * | 2023-04-26 | 2023-05-26 | 中国航空工业集团公司沈阳空气动力研究所 | Icing adhesion force measurement system and method for icing wind tunnel test |
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| US3030797A (en) * | 1958-04-30 | 1962-04-24 | Lacks Hyman | Method and apparatus for selection and comparison of the adhesion of ice to surfaces and coatings |
| CN102269691A (en) * | 2011-05-06 | 2011-12-07 | 吉林大学 | Method and apparatus for testing ice adhesion strength |
| CN103776763A (en) * | 2014-01-13 | 2014-05-07 | 南京航空航天大学 | Experiment device and measurement method for measuring adhesive power of rotary cylindrical ice and ice layer |
| CN105277485A (en) * | 2015-09-24 | 2016-01-27 | 空气动力学国家重点实验室 | Ice and object surface adhesion force measuring device |
| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
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2017
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US3030797A (en) * | 1958-04-30 | 1962-04-24 | Lacks Hyman | Method and apparatus for selection and comparison of the adhesion of ice to surfaces and coatings |
| CN102269691A (en) * | 2011-05-06 | 2011-12-07 | 吉林大学 | Method and apparatus for testing ice adhesion strength |
| CN103776763A (en) * | 2014-01-13 | 2014-05-07 | 南京航空航天大学 | Experiment device and measurement method for measuring adhesive power of rotary cylindrical ice and ice layer |
| CN105277485A (en) * | 2015-09-24 | 2016-01-27 | 空气动力学国家重点实验室 | Ice and object surface adhesion force measuring device |
| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110887748A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Ice collection unit, device and device for measuring shear strength between ice layer and fixed wall |
| CN110887748B (en) * | 2019-12-02 | 2022-06-24 | 中国空气动力研究与发展中心 | Ice collecting device and device for measuring shear strength between ice layer and fixed wall |
| CN111076888A (en) * | 2020-01-10 | 2020-04-28 | 北京航空航天大学 | Small vertical backflow ice wind tunnel experimental device for measuring ice accretion adhesion |
| CN111398167A (en) * | 2020-04-24 | 2020-07-10 | 山东大学 | Surface ice adhesion wireless measurement device and method |
| CN111398167B (en) * | 2020-04-24 | 2021-07-27 | 山东大学 | Surface ice adhesion wireless measurement device and method |
| CN113484235A (en) * | 2021-06-25 | 2021-10-08 | 东北农业大学 | Device for measuring ice adhesion strength on surface of wind turbine blade |
| CN113484235B (en) * | 2021-06-25 | 2023-03-14 | 东北农业大学 | Device for measuring ice adhesion strength on surface of wind turbine blade |
| CN115628876A (en) * | 2022-12-08 | 2023-01-20 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN115628876B (en) * | 2022-12-08 | 2023-03-14 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN116164928A (en) * | 2023-04-26 | 2023-05-26 | 中国航空工业集团公司沈阳空气动力研究所 | Icing adhesion force measurement system and method for icing wind tunnel test |
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Effective date of abandoning: 20210312 |