CN112124600A - Anti-icing and deicing coating of composite wing - Google Patents
Anti-icing and deicing coating of composite wing Download PDFInfo
- Publication number
- CN112124600A CN112124600A CN202011058277.1A CN202011058277A CN112124600A CN 112124600 A CN112124600 A CN 112124600A CN 202011058277 A CN202011058277 A CN 202011058277A CN 112124600 A CN112124600 A CN 112124600A
- Authority
- CN
- China
- Prior art keywords
- icing
- coating
- self
- wing
- lubricating
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
- B64D15/22—Automatic initiation by icing detector
Abstract
The invention discloses an anti-icing coating of a composite wing, which comprises a self-lubricating anti-icing coating arranged on the front edge of the wing, an electric heating layer arranged below the self-lubricating anti-icing coating and used for heating the self-lubricating anti-icing coating, a temperature sensor used for detecting the surface temperature of the self-lubricating anti-icing coating, and a controller connected with the temperature sensor and the electric heating layer in a signal mode, wherein when the temperature detected by the temperature sensor is lower than the preset temperature, the controller controls the electric heating layer to heat. The self-lubricating anti-icing coating is combined with the electric heating layer, so that water is not easy to stay on the surface of the wing by the self-lubricating anti-icing coating, and a preliminary anti-icing effect is achieved. When the aircraft meets the severe environment with too low temperature, the self-lubricating anti-icing coating is heated through the electric heating layer to prevent the aircraft wings from icing. The mode of combining passive anti-icing and active anti-icing is adopted, and the anti-icing and anti-icing capacity of the wings is greatly improved.
Description
Technical Field
The invention relates to the technical field of wing ice prevention, in particular to an anti-icing coating of a composite wing.
Background
When the airplane flies in cold air, wings of the airplane are often frozen, and once more ice is generated on the wings, the normal flight of the airplane is affected, and the flight safety of the airplane is dangerous.
In the prior art, in order to prevent the wings of the airplane from being frozen, the self-lubricating anti-icing coating is coated on the front edge of the wings of the airplane, and the water is not easy to stay on the surfaces of the wings by utilizing the property of the self-lubricating anti-icing coating, so that a certain anti-icing effect is achieved.
Therefore, how to further improve the anti-icing effect of the aircraft wing is a problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In view of the above, the invention aims to provide an anti-icing coating for a composite wing, which can remarkably improve the anti-icing effect of the wing of an airplane and ensure the flight safety.
In order to achieve the above purpose, the invention provides the following technical scheme:
the utility model provides a prevent and remove ice coating of compound wing, is including the self-lubricating anti-icing coating of locating the wing leading edge and locate self-lubricating anti-icing coating below and be used for right the self-lubricating anti-icing coating carries out the electric heating layer that heats, is used for detecting the surface temperature's of self-lubricating anti-icing coating temperature sensor and signal connection in temperature sensor with the controller of electric heating layer works as when the temperature that temperature sensor detected is less than preset temperature, controller control the electric heating layer heats.
Preferably, the electric heating layer includes the regional zone of heating that a plurality of sections set up along the length direction segmentation of wing leading edge, corresponds every the top of regional zone of heating self-lubricating anti-icing coating department all is equipped with one temperature sensor works as the temperature that detects that temperature sensor detects is less than during the preset temperature, controller control corresponds the temperature sensor below the regional zone of heating heats.
Preferably, the regional heating layer includes the electric heat coating of locating the wing leading edge, lays the parallel electrode of the upper and lower both sides of wing leading edge, the parallel electrode includes positive electrode and negative electrode, the positive electrode with the negative electrode is located the electric heat coating both ends, just the positive electrode with the negative electrode is connected respectively in the positive pole and the negative pole of power.
Preferably, the controller comprises manual control buttons in one-to-one correspondence with the area heating layers, and the manual control buttons are used for controlling opening and closing of the area heating layers.
Preferably, the preset temperature is 0 ℃.
Preferably, an insulating coating is arranged between the electrothermal coating and the leading edge of the wing.
Preferably, a protective coating is arranged between the electric heating coating and the self-lubricating anti-icing coating.
Preferably, the protective coating is an aviation special finish.
The composite type wing anti-icing coating provided by the invention adopts a mode of combining the self-lubricating anti-icing coating and the electric heating layer, and utilizes the physical characteristics of the self-lubricating anti-icing coating to ensure that water is not easy to remain on the surface of the wing so as to play a primary anti-icing role. When the aircraft meets the severe environment with too low temperature, the self-lubricating anti-icing coating is heated through the electric heating layer to prevent the aircraft wings from icing. The invention combines the anti-icing and self-lubricating anti-icing coatings of the electric heating layer, adopts the combination of passive anti-icing and active anti-icing, adopts dual-redundancy design, ensures the safety of the wings when the single anti-icing and anti-icing functions fail in the complex meteorological environment, greatly improves the anti-icing and anti-icing capacity of the wings and improves the safety of the wings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic illustration of an anti-icing coating for a composite airfoil provided in accordance with the present invention applied to an aircraft;
FIG. 2 is a partial schematic view of FIG. 1;
fig. 3 is a schematic diagram of a parallel electrode arrangement.
The self-lubricating anti-icing coating comprises a wing leading edge, a self-lubricating anti-icing coating, a protective coating, an electrothermal coating, an insulating coating and a parallel electrode, wherein the wing leading edge is 11, the electrothermal coating is 13, and the insulating coating is 14.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The core of the invention is to provide the anti-icing and deicing coating of the composite wing, which can obviously improve the anti-icing effect of the wing of the airplane and ensure the flight safety.
Referring to fig. 1 to 3, fig. 1 is a schematic view illustrating an anti-icing coating for a composite wing according to the present invention applied to an aircraft; FIG. 2 is a partial schematic view of FIG. 1; fig. 3 is a schematic diagram of a parallel electrode arrangement.
The composite type wing anti-icing coating provided by the invention comprises a self-lubricating anti-icing coating 11 arranged on the front edge 1 of the wing, an electric heating layer arranged below the self-lubricating anti-icing coating 11 and used for heating the self-lubricating anti-icing coating 11, a temperature sensor used for detecting the surface temperature of the self-lubricating anti-icing coating 11, and a controller connected with the temperature sensor and the electric heating layer in a signal mode, wherein when the temperature detected by the temperature sensor is lower than the preset temperature, the controller controls the electric heating layer to heat.
The self-lubricating anti-icing coating 11 is arranged on the outermost layer of the wing leading edge 1, and water is not easy to stay on the surface of the wing by utilizing the material property of the self-lubricating anti-icing coating 11, so that the effect of preliminary water and ice prevention is achieved.
An electric heating layer is arranged below the self-lubricating anti-icing coating 11, and the electrode thermal layer can heat the self-lubricating anti-icing coating 11 when needed, so that the phenomenon that the surface temperature of the self-lubricating anti-icing coating 11 is too low to cause the direct icing of the water vapor on the wing is prevented.
Temperature sensor is used for detecting self-lubricating anti-icing coating 11's surface temperature to the cooperation controller is controlled the electric heating layer, and when the temperature that temperature sensor detected was less than preset temperature, also when the surface temperature of self-lubricating was less than preset temperature, then the controller alright control electric heating layer and open, in order to heat self-lubricating anti-icing coating 11, thereby, avoid self-lubricating anti-icing coating 11's surface temperature to hang down excessively.
The composite type wing anti-icing coating provided by the invention adopts a mode of combining the self-lubricating anti-icing coating 11 and the electric heating layer, and utilizes the physical characteristics of the self-lubricating anti-icing coating 11 to ensure that water is not easy to remain on the surface of the wing so as to play a role of preliminary anti-icing. When the aircraft meets a severe environment with too low temperature, the self-lubricating anti-icing coating 11 is heated by the electric heating layer to prevent the wings from icing. The mode of combining the electric heating layer anti-icing and the self-lubricating anti-icing coating 11 is a mode of combining passive anti-icing and active anti-icing, and the dual-redundancy design ensures the safety of the wings when the single anti-icing and anti-icing functions fail in a complex meteorological environment, greatly improves the anti-icing and anti-icing capacity of the wings and improves the safety of the wings.
On the basis of the above embodiment, as an optimization, the electric heating layer includes a plurality of regional heating layers that set up along the length direction segmentation of wing leading edge 1 for a section, and the self-lubricating anti-icing coating 11 department that corresponds the top of every regional heating layer all is equipped with a temperature sensor, and when the temperature that detects that temperature sensor detects was less than preset temperature, the regional heating layer that corresponds the temperature sensor below was controlled to the controller and is heated.
In the embodiment, considering that the wing span exceeds 20 meters, the wing root protection area is large, the wing tip is small, the average coating arc length is calculated according to 25cm, the area of the wing to be heated is not lower than 5 square meters, the wing is designed according to 0.3W per square centimeter, the total power reaches 15kW, and considering current limitation, the single-side wing is subjected to sectional design and spraying. The length of the single-side wing is about 10 meters, the single-side wing can be divided into nine sections along the length direction, and the zoning design, the zoning spraying and the zoning control are carried out.
Specifically, every section regional utensil is equipped with regional zone of heating, every regional zone of heating connects respectively in the controller, carry out independent control to each regional zone of heating through the controller, and the self-lubricating anti-icing coating 11 department of the top of every regional zone of heating all is equipped with a temperature sensor, temperature sensor and regional zone of heating one-to-one promptly, when the temperature that one of them temperature sensor detected was less than preset the temperature, then the regional zone of heating that this temperature sensor of controller control corresponds is opened, in order to heat self-lubricating anti-icing coating 11 above that.
Thereby, can control one or several regional zone of heating layer work wherein as required, avoid all regional zone of heating layer simultaneous working and lead to the too big problem of consumed power, thereby can improve the security of electric heating layer's use, and through the mode of segmentation heating, can reduce the risk that electric heating layer broke down, because each section regional zone of heating is mutually independent, consequently, when some regional zone of heating broke down, all the other regional zone of heating still can continue to work, thereby, reduce electric heating layer local failure and lead to the probability that the wing freezes.
On the basis of the above embodiment, as a preferable mode, the area heating layer includes an electrothermal coating layer 13 disposed on the leading edge 1 of the airfoil, and parallel electrodes 15 laid on the upper and lower sides of the leading edge 1 of the airfoil, where the parallel electrodes 15 include a positive electrode and a negative electrode, the positive electrode and the negative electrode are disposed at two ends of the electrothermal coating layer 13, and the positive electrode and the negative electrode are respectively connected to a positive electrode and a negative electrode of a power supply.
In this embodiment, in view of the specific arrangement mode of the area heating layer, specifically, the area heating layer includes the electric heating coating 13, and a parallel electrode is respectively laid on the upper and lower sides of the wing leading edge 1, and is a positive electrode and a negative electrode respectively, the positive electrode is connected to the positive pole of the power supply, the negative pole is connected to the negative pole of the power supply, the two electrodes are parallel to each other, and the positive electrode and the negative electrode are located at the two ends of the electric heating coating 13 respectively, so that the resistance wire in the electric heating coating 13 generates heat to heat the self-lubricating coating.
In addition, the controller can include control box and block terminal, and the cooperation box is used for positive electrode and negative electrode distribution, and the control box is used for controlling the block terminal to the realization is controlled opening and close of regional zone of heating work. The control box and the distribution box can be arranged in the middle belly equipment cabin. The distribution box is divided into a left distribution box and a right distribution box which are respectively arranged in the left power supply nacelle and the right power supply nacelle. The single-side distribution box supplies the electric energy of the single-side power supply pod to the electrothermal coating 13 of the single-side wing respectively according to the instruction of the control box.
On the basis of the above embodiments, in consideration of the specific arrangement manner of the controller, as a preferable mode, the controller includes manual control buttons in one-to-one correspondence with the area heating layers, and the manual control buttons are used for controlling the on and off of the corresponding area heating layers.
That is, in this embodiment, the controller includes manual control button, and manual control button is used for the opening and closing of active control regional zone of heating, and manual control button and regional zone of heating one-to-one to regional zone of heating carries out manual control to certain region of heating when needs, for example, operating personnel observes the wing through surveillance camera machine and has the condition of icing, then can directly carry out manual control through manual control button.
On the basis of the above-described embodiment, in consideration of the specific value of the preset temperature, it is preferable that the preset temperature is 0 ℃. Of course, other temperatures may be provided as desired.
On the basis of the above-described embodiment, an insulating coating 14 is preferably provided between the electrothermal coating 13 and the leading edge 1 of the airfoil. That is, in this embodiment, the insulating coating 14 is disposed between the leading edge 1 of the wing and the electrothermal coating 13, and specifically, the insulating coating 14 may be an insulating topcoat to prevent the electrothermal coating 13 from leaking electricity. Specifically, the insulating coating 14 has two layers, the bottom is glass cloth and DG-3 glue, and the upper surface is sprayed with a layer of aviation special primer.
On the basis of the above embodiment, as a preferable mode, a protective coating 12 is provided between the electrothermal coating 13 and the self-lubricating anti-icing coating 11. In this embodiment, set up protective coating 12 between electric heat coating 13 and self-lubricating anti-icing coating 11 to heat self-lubricating anti-icing coating 11 through indirect heating's mode, prevent that self-lubricating anti-icing coating 11 from directly being heated and damaging or warping. Specifically, the protective coating 12 may be an aviation-specific topcoat.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The detailed description of the anti-icing coating of the composite wing provided by the invention is provided above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
1. The utility model provides a prevent icing-out coating of compound wing, its characterized in that, including self-lubricating anti-icing coating (11) of locating wing leading edge (1) and locate self-lubricating anti-icing coating (11) below and be used for right self-lubricating anti-icing coating (11) carry out the electric heating layer that heats, be used for detecting the temperature sensor and the signal connection of the surface temperature of self-lubricating anti-icing coating (11) in temperature sensor with the controller of electric heating layer works as when the temperature that temperature sensor detected is less than preset temperature, controller control the electric heating layer heats.
2. An anti-icing coating for a composite wing according to claim 1, wherein the electric heating layer comprises a plurality of sections of regional heating layers which are arranged along the length direction of the wing leading edge (1) in a segmented manner, one temperature sensor is arranged at the self-lubricating anti-icing coating (11) corresponding to the upper part of each regional heating layer, and when the detected temperature detected by the temperature sensor is lower than the preset temperature, the controller controls the regional heating layers corresponding to the lower parts of the temperature sensors to be heated.
3. The anti-icing and anti-icing coating for the composite wing according to claim 2, wherein the area heating layer comprises an electrothermal coating (13) arranged on the wing leading edge (1) and parallel electrodes (15) laid on the upper side and the lower side of the wing leading edge (1), the parallel electrodes (15) comprise a positive electrode and a negative electrode, the positive electrode and the negative electrode are arranged at two ends of the electrothermal coating (13), and the positive electrode and the negative electrode are respectively connected to a positive electrode and a negative electrode of a power supply.
4. The anti-icing coating for the composite type wing according to claim 3, wherein the controller comprises manual control buttons which correspond to the area heating layers in a one-to-one mode, and the manual control buttons are used for controlling the opening and closing of the area heating layers.
5. An anti-icing coating for a composite airfoil as claimed in claim 4, wherein the predetermined temperature is 0 ℃.
6. A composite airfoil anti-icing coating according to any one of claims 2 to 5, characterised in that an insulating coating (14) is provided between the electrothermal coating (13) and the airfoil leading edge (1).
7. An anti-icing coating for a composite wing according to claim 6, characterised in that a protective coating (12) is provided between the electrothermal coating (13) and the self-lubricating anti-icing coating (11).
8. The anti-icing coating for a composite wing according to claim 7, characterized in that the protective coating (12) is an aviation-specific topcoat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011058277.1A CN112124600A (en) | 2020-09-30 | 2020-09-30 | Anti-icing and deicing coating of composite wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011058277.1A CN112124600A (en) | 2020-09-30 | 2020-09-30 | Anti-icing and deicing coating of composite wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112124600A true CN112124600A (en) | 2020-12-25 |
Family
ID=73843399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011058277.1A Pending CN112124600A (en) | 2020-09-30 | 2020-09-30 | Anti-icing and deicing coating of composite wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112124600A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113266540A (en) * | 2021-06-21 | 2021-08-17 | 中能电力科技开发有限公司 | Anti-icing and deicing method for composite coating of fan blade |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050184193A1 (en) * | 2003-12-12 | 2005-08-25 | Eurocopter | Modular anti-icing/de-icing device for an aerodynamic surface |
| CN201665809U (en) * | 2010-03-15 | 2010-12-08 | 邵建人 | Anti-freezing airport pavement surface structure |
| US20110049300A1 (en) * | 2009-09-03 | 2011-03-03 | The Boeing Company | Ice Protection System And Method |
| CN104443396A (en) * | 2014-12-10 | 2015-03-25 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Surface ice protection system for composite airfoils |
| CN105032731A (en) * | 2015-08-05 | 2015-11-11 | 北京航空航天大学 | Preparation method for energy-saving anti-icing/deicing coating combining super-hydrophobic coating and heating coating |
| CN106892123A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of electrothermal frontal windshield heating system |
| CN109486332A (en) * | 2018-11-22 | 2019-03-19 | 中国科学院兰州化学物理研究所 | A kind of anti-deicing coating of electric heating self-lubricating and its preparation method and application |
| CN109625289A (en) * | 2018-11-29 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft de-icing device based on solar energy |
| US20190144122A1 (en) * | 2016-05-09 | 2019-05-16 | Eric Loth | Methods and systems for self-lubricating icephobic elastomer coatings |
| CN109794404A (en) * | 2019-01-25 | 2019-05-24 | 南京航空航天大学 | Anti- deicing component of a kind of electric heating with superhydrophobic characteristic and preparation method thereof |
| CN109862637A (en) * | 2019-01-18 | 2019-06-07 | 南京航空航天大学 | A kind of anti-deicing electric heating device and preparation method with graphene-carbon nano tube composite material |
| CN110423523A (en) * | 2019-09-05 | 2019-11-08 | 中国航空制造技术研究院 | A kind of super-hydrophobic deicing composite coating and preparation method thereof |
| 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 |
| CN111645865A (en) * | 2020-07-07 | 2020-09-11 | 江西克莱威纳米碳材料有限公司 | Deicing device for wing skin |
-
2020
- 2020-09-30 CN CN202011058277.1A patent/CN112124600A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050184193A1 (en) * | 2003-12-12 | 2005-08-25 | Eurocopter | Modular anti-icing/de-icing device for an aerodynamic surface |
| US20110049300A1 (en) * | 2009-09-03 | 2011-03-03 | The Boeing Company | Ice Protection System And Method |
| CN201665809U (en) * | 2010-03-15 | 2010-12-08 | 邵建人 | Anti-freezing airport pavement surface structure |
| CN104443396A (en) * | 2014-12-10 | 2015-03-25 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Surface ice protection system for composite airfoils |
| CN105032731A (en) * | 2015-08-05 | 2015-11-11 | 北京航空航天大学 | Preparation method for energy-saving anti-icing/deicing coating combining super-hydrophobic coating and heating coating |
| CN106892123A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of electrothermal frontal windshield heating system |
| US20190144122A1 (en) * | 2016-05-09 | 2019-05-16 | Eric Loth | Methods and systems for self-lubricating icephobic elastomer coatings |
| CN109486332A (en) * | 2018-11-22 | 2019-03-19 | 中国科学院兰州化学物理研究所 | A kind of anti-deicing coating of electric heating self-lubricating and its preparation method and application |
| CN109625289A (en) * | 2018-11-29 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft de-icing device based on solar energy |
| CN109862637A (en) * | 2019-01-18 | 2019-06-07 | 南京航空航天大学 | A kind of anti-deicing electric heating device and preparation method with graphene-carbon nano tube composite material |
| CN109794404A (en) * | 2019-01-25 | 2019-05-24 | 南京航空航天大学 | Anti- deicing component of a kind of electric heating with superhydrophobic characteristic and preparation method thereof |
| CN110423523A (en) * | 2019-09-05 | 2019-11-08 | 中国航空制造技术研究院 | A kind of super-hydrophobic deicing composite coating and preparation method thereof |
| 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 |
| CN111645865A (en) * | 2020-07-07 | 2020-09-11 | 江西克莱威纳米碳材料有限公司 | Deicing device for wing skin |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113266540A (en) * | 2021-06-21 | 2021-08-17 | 中能电力科技开发有限公司 | Anti-icing and deicing method for composite coating of fan blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2379258C (en) | Redundant de-icing/anti-icing system for aircraft | |
| US7124983B2 (en) | Hybrid electrical ice protection system and method including an energy saving mode | |
| EP2195238B1 (en) | Ice protection heater system | |
| CN107745816B (en) | A kind of aircraft wing automatic deicer | |
| CN107084100B (en) | Wind power blade heating and ice melting system based on graphene heating film and manufacturing method of blade | |
| CN112193421A (en) | Electric heating coating for preventing and removing ice on wing | |
| CN109625289B (en) | Deicing device is prevented to aircraft based on solar energy | |
| CN109281807B (en) | Wind power blade deicing system and control method thereof | |
| CN114261523B (en) | Combined deicing system | |
| CN101695959A (en) | Ice preventing and removing device for helicopter rotors | |
| US20160025069A1 (en) | Wind turbine and method for operating a wind turbine | |
| CN107985607A (en) | A kind of unmanned plane icing protective device | |
| CN107120243A (en) | A kind of wind electricity blade preparation method that ice-melt is heated based on graphene | |
| CN112124600A (en) | Anti-icing and deicing coating of composite wing | |
| CN110510102B (en) | Attachable self-resistance heating/super-hydrophobic integrated gradient film material | |
| CN109334998A (en) | A kind of gradient distribution formula plasma de-icing device and method | |
| CN110481792A (en) | A kind of novel plasma ice shape regulation device, method and anti-freeze type aircraft | |
| EP1873060A1 (en) | Hybrid electrical ice protection system and method including an energy saving mode | |
| CN113148183A (en) | Plasma hot knife and hydrophobic material combined type deicing device and application | |
| CN112572808B (en) | Double-layer anti-icing and electric heating structure and wing adopting same | |
| CN107117319B (en) | One kind preventing/deicing composite material by multilayer structure | |
| CN212921989U (en) | Deicing device for aircraft | |
| CN112298548A (en) | Rotor and unmanned helicopter with prevent and remove ice function | |
| CN208106668U (en) | A kind of wind electricity blade appearance facial mask structure heating deicing system | |
| CN110963045A (en) | Automatic anti-icing and deicing device for fuel wing of aircraft and working method of automatic anti-icing and deicing device |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201225 |