CN114933018B - Airplane deicing device and method based on liquid drop directional movement - Google Patents
Airplane deicing device and method based on liquid drop directional movement Download PDFInfo
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- CN114933018B CN114933018B CN202210599451.6A CN202210599451A CN114933018B CN 114933018 B CN114933018 B CN 114933018B CN 202210599451 A CN202210599451 A CN 202210599451A CN 114933018 B CN114933018 B CN 114933018B
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- 239000007788 liquid Substances 0.000 title claims abstract description 54
- 230000026058 directional locomotion Effects 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 22
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 41
- 238000010438 heat treatment Methods 0.000 claims description 25
- 230000008569 process Effects 0.000 claims description 10
- 230000009471 action Effects 0.000 claims description 7
- 230000002209 hydrophobic effect Effects 0.000 claims description 7
- 239000007787 solid Substances 0.000 claims description 7
- 238000012546 transfer Methods 0.000 claims description 5
- 238000000206 photolithography Methods 0.000 claims description 2
- 230000002265 prevention Effects 0.000 description 7
- 238000005265 energy consumption Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 238000001259 photo etching Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000002528 anti-freeze Effects 0.000 description 2
- 238000003912 environmental pollution Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 241000826860 Trapezium Species 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000009877 rendering Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses an aircraft deicing device and method based on directional movement of liquid drops, which belong to the technical field of aircraft deicing, and comprise a surface energy gradient surface arranged on the front end surface of an airfoil, wherein the surface energy gradient surface is connected with a water collecting area to form a funnel shape; the surface energy gradient surface comprises a plurality of rows of high surface energy areas, the high surface energy areas are arranged in a triangular shape, each high surface energy area is provided with a plurality of rows of equilateral triangle structures, and each equilateral triangle structure and each high surface energy area are provided with a corner facing the water collecting area. The surface energy gradient surface has gradient surface energy, and liquid drops striking on the wing can spontaneously move to a region with high surface energy, so that the directional movement and collection of the liquid drops are realized, and the liquid drops can be collected in a water collecting region behind the gradient surface.
Description
Technical Field
The invention relates to the technical field of aircraft deicing, in particular to an aircraft deicing device and method based on directional movement of liquid drops.
Background
The statements herein merely provide background information related to the present disclosure and may not necessarily constitute prior art.
Aircraft icing is one of the major hazards leading to flight safety accidents. In the flight process, the surface of the wing front edge and other parts is frozen, so that the weight of the aircraft is increased, the aerodynamic shape of the surface of the aircraft is damaged, the bypass flow field is changed, the maximum lift-drag ratio of the aircraft is reduced, the stall attack angle is reduced, the operability and the stability of the aircraft are affected, and even safety accidents are caused in serious cases.
The inventor finds that the existing aircraft deicing method comprises the methods of expansion pipe deicing, common electrothermal deicing prevention, gas-thermal deicing prevention, deicing prevention by antifreeze solution and the like, but brings new problems of influencing aerodynamic appearance, huge energy consumption, environmental pollution and the like. The directional movement of the liquid drops on the surface of the wetting opposite side has important application values, such as oil-water separation, water collection and the like, and becomes a research hot spot in the field of surface interfaces. The droplets are capable of directional movement on the solid surface, mainly because of a certain driving force generated by the surface structure or material property of the droplets, and the droplets are driven to perform directional movement on the solid surface, such as a surface energy gradient, a Laplace pressure gradient and the like.
If the directional movement of the liquid drops can be utilized, the liquid drops are concentrated in a certain area of the wing before icing, and the regional concentrated treatment is carried out, so that the energy consumption can be greatly reduced, and the ice preventing and removing efficiency is improved.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide an airplane deicing device and method based on the directional movement of liquid drops, which are characterized in that the surface of an airplane wing is subjected to surface micro-treatment so as to enable the surface of the wing to have gradient surface energy, and the liquid drops on the wing can spontaneously move to a region with high surface energy on the gradient surface, so that the directional movement and collection of the liquid drops are realized. Finally, the liquid drops can be collected in a water collecting area behind the gradient surface, in the water collecting area, after the liquid drops freeze, a heating device below the wing skin can be started, ice is melted and falls off by heat, a better deicing effect is realized by a smaller heating area and lower power consumption, and the problems that the pneumatic appearance is influenced, the energy consumption is huge and the environment is polluted in the existing aircraft deicing technology are solved.
In order to achieve the above object, the present invention is realized by the following technical scheme:
In a first aspect, the invention provides an aircraft deicing device based on directional movement of liquid drops, comprising a surface energy gradient surface arranged on the front end surface of an airfoil, wherein the surface energy gradient surface is connected with a water collecting area to form a funnel shape; the surface energy gradient surface comprises a plurality of rows of high surface energy areas, the high surface energy areas are arranged in a triangular shape, each high surface energy area is provided with a plurality of rows of equilateral triangle structures, and each equilateral triangle structure and each high surface energy area are provided with a corner facing the water collecting area.
As a further technical solution, the equilateral triangle structure is arranged in a form of hydrophilic strips-hydrophobic strips being spaced.
As a further technical scheme, the hydrophilic strips are arranged in an equilateral triangle structure in parallel with the direction of the airplane body, and the hydrophilic strips are groove-shaped.
As a further technical scheme, each row of the surface energy gradient surface is provided with a plurality of high surface energy areas, the high surface energy areas of adjacent rows are connected, and the adjacent high surface energy areas are mutually communicated.
As a further technical scheme, the equilateral triangle structures of the high surface energy region are sequentially arranged, and adjacent equilateral triangle structures are connected with each other.
As a further technical scheme, the surface energy gradient is trapezoidal, and the water collecting area is rectangular.
As a further technical scheme, a heating device is paved below the skin of the water collecting area.
As a further technical solution, the overall surface energy of the surface energy gradient plane is higher than that of other areas of the wing.
As a further technical scheme, the surface energy gradient surface is obtained by carrying out surface micro-treatment on the surface of the wing through a photoetching process, and the surface energy of the surface energy gradient surface is distributed in a gradient manner.
In a second aspect, the present invention provides a method of operating an aircraft anti-icing device based on directional movement of droplets as described above, comprising the steps of:
when the surface of the wing is adhered with liquid drops, the liquid drops spontaneously move from a low surface energy area to a high surface energy area under the action of solid surface energy and pressure difference, the high surface energy areas are mutually communicated, a groove-type hydrophilic strip with higher hydrophilicity is arranged in the high surface energy area, the liquid drops move along the groove, and when the liquid drops store a set amount in a certain triangular area of the high surface energy area, the liquid drops are transferred to the next triangle; through successive transfer processes, the droplets are eventually collected in a water collection zone;
when the liquid drops freeze, a heating device paved below the skin of the water collecting area is electrified and heated, and the accumulated ice is melted, so that the accumulated ice falls off.
The beneficial effects of the invention are as follows:
According to the invention, the surface micro-treatment is carried out on the aircraft wing to form the surface energy gradient surface, so that the surface of the wing has gradient surface energy, and on the gradient surface, liquid drops striking on the wing can spontaneously move to a region with high surface energy, so that the directional movement and collection of the liquid drops are realized. Finally, the liquid drops can be collected in a water collecting area behind the gradient surface, in the water collecting area, after the liquid drops freeze, a heating device below the wing skin can be started, ice is melted and falls off by heat, the power consumption of thermal deicing is greatly reduced, and better deicing effect is realized by a smaller heating area and lower power consumption.
The surface energy gradient surface is manufactured by carrying out surface micro-treatment on the surface of the wing through a photoetching technology, the surface shape of the wing is not changed, the aerodynamic appearance is protected, the damage of a bypass flow field is avoided, the phenomena of reduction of the maximum lift-drag ratio and the stall attack angle of the aircraft are not caused, and the operability and the stability of the aircraft are ensured.
The liquid drops on the surface of the wing can spontaneously move from a low surface energy area to a high surface energy area under the action of the solid surface energy and Laplace pressure difference, and are directionally collected to a water collecting area under the guiding action of the groove type hydrophilic strips, so that the energy consumption is greatly reduced.
The heating device is arranged below the skin, so that the structure and the shape of the outer surface of the wing are not changed, the aerodynamic shape of the wing is protected, the influence on the bypass flow field is avoided, and the operability and the stability of the aircraft are ensured.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention.
FIG. 1 is a schematic overall structural view of a surface energy gradient surface and heating zone of an aircraft anti-icing assembly based on directional movement of droplets in accordance with one or more embodiments of the present invention;
FIG. 2 is a schematic illustration of specific configurations of surface energy gradient facets and heating zones and droplet motion directions in accordance with one or more embodiments of the present invention;
FIG. 3 is a schematic view of a high surface energy region structure in accordance with one or more embodiments of the present invention;
In the figure: the mutual spacing or size is exaggerated for showing the positions of all parts, and the schematic drawings are used only for illustration;
wherein, 1, the wing; 2. a surface energy gradient surface; 3. a water collection zone; 4. a high surface energy region; 5. a heating device; 6. hydrophilic strips.
Detailed Description
It should be noted that the following detailed description is illustrative and is intended to provide further explanation of the invention. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
As described in the background art, the existing aircraft deicing method comprises the methods of expansion pipe deicing, common electrothermal deicing prevention, gas-heat deicing prevention, deicing prevention by antifreeze solution and the like, but the novel problems of influence on aerodynamic appearance, huge energy consumption, environmental pollution and the like are brought along, and in order to solve the technical problems, the invention provides an aircraft deicing device and method based on the directional movement of liquid drops.
Example 1
In an exemplary embodiment of the invention, as shown in fig. 1-3, an aircraft anti-icing device based on directional movement of droplets is proposed, comprising a surface energy gradient surface 2 provided on the surface of an airfoil 1 and a water collection zone 3.
The surface energy gradient surface 2 is positioned at the front end of the wing 1, namely, at one side close to the flying direction, the surface energy gradient surface 2 is manufactured by carrying out surface micro-treatment on the surface of the wing 1 through a photoetching technology, and the surface energy of the surface energy gradient surface 2 is in gradient distribution.
In order to enable the droplet to roll towards the surface energy gradient 2, the leading edge of the wing 1 needs to be machined to a hydrophobic region, so that during flight, when the droplet hits the leading edge of the wing, the droplet rolls to the surface energy gradient 2 under inertial forces.
The specific form of the surface energy gradient surface 2 is as follows: by means of photolithography, areas with different surface energies are machined into the upper surface of the wing 1, whereby a surface energy gradient is formed. In the high surface energy region, hydrophilicity is presented; rendering hydrophobic in the low surface energy region. Wherein the overall surface energy of the surface energy gradient 2 is higher than in other regions of the wing 1.
The surface energy gradient surface 2 is arranged in a photoetching mode, the shape of the wing 1 is not changed, the aerodynamic shape is protected, the damage of a bypass flow field is avoided, the phenomena of the reduction of the maximum lift-drag ratio and the stall attack angle of the aircraft are not caused, and the operability and the stability of the aircraft are ensured.
Since the wing 1 is overall hydrophilic-hydrophobic in morphology, the contact angle of the droplet with the surface of the wing 1 is different when the droplet falls on different morphologies. In the hydrophobic region, the contact angle of the droplet will be greater than in the hydrophilic region, i.e. the droplet in the hydrophobic region is more spherical. When the liquid drop is at the hydrophilic-hydrophobic junction, the contact angles of the two sides are different, so that the generated Laplace pressure difference is also different, namely the liquid drop spontaneously moves from the hydrophobic area to the hydrophilic area under the action force generated by the geometrical shape of the liquid drop, and the liquid drop is integrally gathered from the front edge of the wing 1 to the surface energy gradient surface 2 area.
As shown in fig. 2, the surface energy gradient surface 2 and the water collecting area 3 are connected and form a funnel shape, the front half part of the funnel is the surface energy gradient surface 2 with a trapezoid shape, and the rear half part of the funnel is the water collecting area 3 with a rectangular shape. The long bottom side of the trapezoid of the surface energy gradient surface 2 is close to the front edge of the wing, and the short bottom side of the trapezoid is close to the rear edge of the wing.
Wherein the surface energy gradient surface 2 is composed of a plurality of high surface energy regions 4, and the plurality of high surface energy regions 4 are uniformly distributed on the surface energy gradient surface 2.
In this embodiment, the high surface energy regions 4 are arranged in a triangle shape, the high surface energy regions 4 are arranged in a plurality of rows on the surface energy gradient surface, each row has a plurality of high surface energy regions 4, the high surface energy regions 4 of the upper row and the lower row are connected, and a triangle is also formed between the adjacent high surface energy regions 4, one corner of the high surface energy regions 4 is arranged towards the rear side of the wing, that is, towards the water collecting area, and the liquid drops are gradually collected towards the water collecting area by the arrangement of the plurality of rows of high surface energy regions.
Specifically, each high surface energy region 4 is composed of 3 equilateral triangle structures with the same shape, the 3 equilateral triangle structures are respectively arranged at three corners of the high surface energy region 4 in an inverted mode and are connected with each other, and one corner of each equilateral triangle is arranged towards the rear side of the wing, namely towards the water collecting area; the arrangement of the adjacent high surface energy regions 4 is the same as that of the equilateral triangle in the interior thereof, each row of the high surface energy regions 4 are arranged in parallel, the adjacent high surface energy regions 4 are communicated with each other, and each high surface energy region 4 is arranged upside down, so that one angle of the high surface energy regions 4 points to the rear side of the wing 1.
This arrangement results in the overall surface energy of the high surface energy regions 4 distributed in the region of the trapezoidal surface energy gradient surface 2 being higher than in the other regions of the trapezoidal surface energy gradient surface 2, and the droplets spontaneously move from the low surface energy regions to the high surface energy regions 4 under the influence of the solid surface energy and the Laplace pressure difference, and because the high surface energy regions 4 are in communication with each other, the droplets are transferred between the surface energy regions 4.
The inverted triangle structure increases the contact area between the high surface energy region 4 and the water drops at the front edge of the wing 1, can collect the water drops better, and plays a role in guiding, so that the water drops are guided to the rear side of the wing 1.
In order to better enable the spontaneous transfer of the droplets to the rear side of the wing 1, the equilateral triangle structure in the high surface energy region 4 is arranged in a form of alternating hydrophilic strips and hydrophobic strips, the hydrophilic strips 6 are arranged on the equilateral triangle structure along the direction parallel to the aircraft fuselage, the hydrophilic strips 6 are in a groove shape, the width of a single groove is smaller than the diameter of the droplets, namely each droplet spans multiple micro grooves, and the droplets can move along the grooves.
When a certain amount of liquid drops are stored in one equilateral triangle structure of the high surface energy region 4, the liquid drops are transferred to the next equilateral triangle structure, and through the successive transfer process, the liquid drops are finally collected in the water collecting region 3, namely the internal surface energy of the high surface energy region 4 is larger, the external surface energy is smaller, the liquid drops move in the high surface energy region 4, and when moving to the connection position with the next high surface energy region 4, the liquid drops enter the next high surface energy region 4 along the connection region.
The working principle is as follows: in the trapezoid area of the surface energy gradient surface 2, the contact angle of the liquid drop in different areas is different due to the existence of the surface energy gradient, and the liquid drop can be gathered to the hydrophilic area under the self pressure difference. While in each equilateral triangle structure of the high surface energy region 4 inside the trapezium, micro-grooves parallel to the direction of the aircraft fuselage are added. The width of the grooves is smaller than the width of the droplets, and when the droplets are in these groove areas, the droplets tend to move more easily along the grooves than perpendicular to the grooves due to the different energy barriers along the grooves and perpendicular to the grooves, the grooves themselves being hydrophilic and the capillary forces between the grooves and the droplets being added, the droplets will gather along the grooves towards the trailing edge of the wing 1.
The water collecting area 3 is of a rectangular structure, the heating device 5 is paved below the skin of the water collecting area 3, when liquid drops freeze in the water collecting area 3, the heating device 5 below the skin works, ice is melted and falls off through heat, deicing of the wing is achieved, the heating device is arranged below the skin, the shape of the outer surface of the wing 1 cannot be changed, and the aerodynamic appearance is protected.
It can be appreciated that the heating device in this embodiment may be a heating wire, a heating plate, an electrothermal tube, an electrothermal rod, or the like, so long as the heating device can be conveniently installed under the wing skin without affecting the aerodynamic shape, and no excessive limitation is made here.
Under the combined action of the surface energy gradient surface 2 and the water collecting area 3, the liquid drops can undergo a collecting-guiding-collecting process, the whole process is carried out spontaneously, the energy consumption is reduced, the liquid drops can be finally collected at the water collecting area 3, and when icing occurs, ice prevention and removal with a smaller heating area and lower power consumption are realized through the heating device 5 below the skin.
The specific treatment process of the liquid drops on the upper surface of the wing 1 is as follows:
when the aircraft passes through the cloud layer containing the liquid drops, the liquid drops adhere to the surface of the wing 1;
The droplets spontaneously move from the low surface energy region to the high surface energy region 4 under the action of the solid surface energy and Laplace pressure difference, the high surface energy regions 4 are communicated with each other, the inside of the high surface energy region is provided with groove-type hydrophilic strips 6 with higher hydrophilicity, the droplets move along the grooves, and the droplets are transferred to the next triangle when the droplets are stored for a certain amount in one triangle region of the high surface energy region 4. Through successive transfer processes, the droplets are eventually collected in the water collection zone 3;
heating devices 5 such as heating wires are paved below the skin of the water collecting area 3, and when the liquid drops freeze, the heating devices 5 are electrified to heat, and the accumulated ice is melted, so that the accumulated ice falls off.
The invention can greatly reduce the power consumption of the thermal deicing scheme in the existing aircraft deicing technology, and realize better deicing effect with smaller heating area and lower power consumption.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The aircraft deicing device based on the directional movement of liquid drops is characterized by comprising a surface energy gradient surface arranged on the front end surface of an airfoil, wherein the surface energy gradient surface is connected with a water collecting area to form a funnel shape; the surface energy gradient surface comprises a plurality of rows of high surface energy areas which are arranged in a triangular shape, each high surface energy area is provided with a plurality of rows of equilateral triangle structures, and each equilateral triangle structure and each high surface energy area are provided with a corner which faces the water collecting area;
The equilateral triangle structure is arranged in a form of alternate hydrophilic strips and hydrophobic strips;
the hydrophilic strips are arranged in the equilateral triangle structure in parallel with the direction of the aircraft body, and are groove-shaped;
the equilateral triangle structures of the high surface energy areas are sequentially arranged, and adjacent equilateral triangle structures are connected with each other;
And a heating device is paved below the skin of the water collecting area.
2. An aircraft anti-ice and deicing apparatus based on directional movement of droplets, as recited in claim 1, wherein said surface energy gradient surfaces are provided with a plurality of high surface energy regions per row, adjacent rows of high surface energy regions meeting, adjacent high surface energy regions communicating with each other.
3. An aircraft anti-ice and water apparatus based on directional movement of droplets according to claim 1, wherein said surface energy gradient is trapezoidal and said water collection area is rectangular.
4. An aircraft anti-icing device based on directional movement of droplets as claimed in claim 1 wherein said surface energy gradient is higher overall surface energy than other areas of the wing.
5. An aircraft deicing apparatus based on directional movement of droplets according to claim 1, wherein said surface energy gradient surface is obtained by subjecting the surface of the airfoil to a surface micro-treatment by a photolithography process, and the surface energy of the surface energy gradient surface is distributed in a gradient manner.
6. A method of operating an aircraft anti-ice device based on directional movement of droplets as claimed in claim 1, comprising the steps of:
when the surface of the wing is adhered with liquid drops, the liquid drops spontaneously move from a low surface energy area to a high surface energy area under the action of solid surface energy and pressure difference, the high surface energy areas are mutually communicated, a groove-type hydrophilic strip with higher hydrophilicity is arranged in the high surface energy area, the liquid drops move along the groove, and when the liquid drops store a set amount in a certain triangular area of the high surface energy area, the liquid drops are transferred to the next triangle; through successive transfer processes, the droplets are eventually collected in a water collection zone;
when the liquid drops freeze, a heating device paved below the skin of the water collecting area is electrified and heated, and the accumulated ice is melted, so that the accumulated ice falls off.
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| CN202210599451.6A CN114933018B (en) | 2022-05-30 | 2022-05-30 | Airplane deicing device and method based on liquid drop directional movement |
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| CN202210599451.6A CN114933018B (en) | 2022-05-30 | 2022-05-30 | Airplane deicing device and method based on liquid drop directional movement |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1105943A (en) * | 1992-10-29 | 1995-08-02 | B.F.谷德里奇公司 | Improved leading edge pneumatic deicer assembly |
| WO2008121418A1 (en) * | 2007-03-30 | 2008-10-09 | The University Of Alabama | A passive drag modification system |
| WO2010010102A2 (en) * | 2008-07-22 | 2010-01-28 | Commissariat A L'energie Atomique | Device for varying the pressure of a pneumatic fluid by displacing drops of liquid and heat pump using such a device |
| WO2013033654A1 (en) * | 2011-08-31 | 2013-03-07 | De Rochemont L Pierre | Fully integrated thermoelectric devices and their application to aerospace de-icing systems |
| CN108052729A (en) * | 2017-12-11 | 2018-05-18 | 中国科学院长春光学精密机械与物理研究所 | The Reverse Design of super hydrophobic surface micro-structure |
| CN108190001A (en) * | 2017-12-29 | 2018-06-22 | 西北工业大学 | A kind of anti-deicing covering in novel subregion |
| CN110316385A (en) * | 2018-03-28 | 2019-10-11 | 拉季埃-菲雅克有限责任公司 | Deicing equipment |
| CN110510102A (en) * | 2019-08-16 | 2019-11-29 | 南京航空航天大学 | A kind of sticking type is from hindering heating/super-hydrophobic integral gradient thin-film material |
| CN110834734A (en) * | 2019-11-14 | 2020-02-25 | 中国人民解放军63831部队 | Deicing system is prevented to wing |
| CN111379767A (en) * | 2020-02-17 | 2020-07-07 | 常熟理工学院 | Surface structure for non-drop height directional liquid transportation |
| CN112935571A (en) * | 2021-03-29 | 2021-06-11 | 南京航空航天大学 | Anti-icing functional structure and preparation method and application thereof |
| US11198513B1 (en) * | 2018-08-03 | 2021-12-14 | Astroseal Products Mfg. Corporation | Anti-icing/de-icing system and method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100330340A1 (en) * | 2009-05-12 | 2010-12-30 | University Of Massachusetts | Superhydrophobic surfaces for drag reduction |
| WO2018148353A1 (en) * | 2017-02-09 | 2018-08-16 | Waters Technologies Corporation | Coordinated composition gradient and temperature gradient liquid chromatography |
-
2022
- 2022-05-30 CN CN202210599451.6A patent/CN114933018B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1105943A (en) * | 1992-10-29 | 1995-08-02 | B.F.谷德里奇公司 | Improved leading edge pneumatic deicer assembly |
| WO2008121418A1 (en) * | 2007-03-30 | 2008-10-09 | The University Of Alabama | A passive drag modification system |
| WO2010010102A2 (en) * | 2008-07-22 | 2010-01-28 | Commissariat A L'energie Atomique | Device for varying the pressure of a pneumatic fluid by displacing drops of liquid and heat pump using such a device |
| WO2013033654A1 (en) * | 2011-08-31 | 2013-03-07 | De Rochemont L Pierre | Fully integrated thermoelectric devices and their application to aerospace de-icing systems |
| CN108052729A (en) * | 2017-12-11 | 2018-05-18 | 中国科学院长春光学精密机械与物理研究所 | The Reverse Design of super hydrophobic surface micro-structure |
| CN108190001A (en) * | 2017-12-29 | 2018-06-22 | 西北工业大学 | A kind of anti-deicing covering in novel subregion |
| CN110316385A (en) * | 2018-03-28 | 2019-10-11 | 拉季埃-菲雅克有限责任公司 | Deicing equipment |
| US11198513B1 (en) * | 2018-08-03 | 2021-12-14 | Astroseal Products Mfg. Corporation | Anti-icing/de-icing system and method |
| CN110510102A (en) * | 2019-08-16 | 2019-11-29 | 南京航空航天大学 | A kind of sticking type is from hindering heating/super-hydrophobic integral gradient thin-film material |
| CN110834734A (en) * | 2019-11-14 | 2020-02-25 | 中国人民解放军63831部队 | Deicing system is prevented to wing |
| CN111379767A (en) * | 2020-02-17 | 2020-07-07 | 常熟理工学院 | Surface structure for non-drop height directional liquid transportation |
| CN112935571A (en) * | 2021-03-29 | 2021-06-11 | 南京航空航天大学 | Anti-icing functional structure and preparation method and application thereof |
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