CN108725802A - It is a kind of for aircraft it is anti-/ electric-heating technology of deicing - Google Patents
It is a kind of for aircraft it is anti-/ electric-heating technology of deicing Download PDFInfo
- Publication number
- CN108725802A CN108725802A CN201710248415.4A CN201710248415A CN108725802A CN 108725802 A CN108725802 A CN 108725802A CN 201710248415 A CN201710248415 A CN 201710248415A CN 108725802 A CN108725802 A CN 108725802A
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- China
- Prior art keywords
- electric
- aircraft
- heating
- electro
- technology
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- 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.)
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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
Abstract
The invention discloses it is a kind of for aircraft it is anti-/ electric-heating technology of deicing, be related to aircraft it is anti-/ clearing ice technology field.The core of electric-heating technology of the present invention is：Electric conductivity electro-thermal coatings are formed on matrix by coating process using electric-heating coatings, electro-thermal coatings constitute complete electrical heating system as heating element and electrical heating power supply, electric-heating control system, icing detection system.This electrical heating system can be used for anti-/ anti-ice operation of aircraft, have the characteristics that be easy to arrange, control it is accurate, efficient and energy saving.
Description
Technical field
The present invention relates to anti-/ clearing ice technology field of aircraft, disclose it is a kind of can be used for aircraft it is anti-/ electricity of deicing adds
Thermal technology.
Background technology
When aircraft enters icing meteorology condition in flight course, certain positions of aircraft surface would generally tie
Ice, for example, helicopter rotor, engine intake, the leading edge of a wing, external inductor of fixed wing aircraft etc.；Work as aircraft
Outdoor park on ground and its surface can generally also freeze when meeting with icing meteorology condition.
The operational safety of aircraft surface icing entail dangers to aircraft.Due to the originals such as available power is limited, control surface is smaller
Cause freezes more dangerous for helicopter.Therefore anti-/ clearing ice technology of development aircraft has great importance.
All aircraft at present it is anti-/ clearing ice technology in, electroheat technology is undoubtedly most reliable, the highest technology of efficiency.
Under normal conditions, heating element (such as nichrome resistance wire) is arranged in position (such as the aircraft fixed-wing for needing to heat
The rotor etc. of leading edge, helicopter) and carry out preventing/anti-ice operation when needed.But this technology is limited to heating element arrangement
Difficulty is also restricted in practical applications.
Invention content
The object of the present invention is to provide it is a kind of can be used for aircraft it is anti-/ electric-heating technology of deicing, this technology can solve
Certainly or part solves defect existing for background technology.
The technical scheme is that：Using electric-heating coatings, electric-heating coatings, which are coated on aircraft, by coating process needs
Prevent/surface of deicing area on or close to electro-thermal coatings are formed in the level on surface, electro-thermal coatings, which have, preferably leads
Electrically, electro-thermal coatings and electrical heating power supply, electric-heating control system, icing detection system then are connected with conductive channel, with structure
It builds complete aircraft electric heating and prevents/deicing system.The core of this system be use electro-thermal coatings as heating element, and with
Established based on this it is a kind of for aircraft it is anti-/ electric-heating technology of deicing.
Preferably, according to each position of aircraft it is anti-/ the different technologies standard requirement of deicing, can correspondingly build each other solely
Vertical electro-thermal coatings simultaneously keep the electro-thermal coatings in each region insulated from each other, then build anti-/ deicing system independent of each other again with this.
So in this way, the operation of each anti-/ deicing system can be precisely controlled, to reach saving energy under the premise of ensureing aircraft security
The purpose in source.
It preferably, can be in the surface of electro-thermal coatings application heat transmission function again in order to meet the aesthetic feeling requirement of aircraft appearance
Good coating.The color of heat transfer coating can be depending on the coating specification of aircraft appearance, while should have higher heat conduction
Coefficient.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Technical scheme of the present invention is described in detail.Described embodiment is only the section Example of the present invention, rather than
Whole embodiments；These embodiments are exemplary, it is intended to for explaining the present invention, and should not be understood as the limit to the present invention
System.Based on the embodiments of the present invention, those skilled in the art obtained under the premise of not making creative work it is all its
Its embodiment, shall fall within the protection scope of the present invention.
Embodiment one：Electric-heating coatings (such as silver/polyurethane coating) are coated on the up-front table of each blade of lifting airscrew
On face, opens up to coating area about 20%, electro-thermal coatings are formed after solidification.Then by electro-thermal coatings and power supply, control system, detection
System connection prevents/deicing system to build electrical heating.The heat that electro-thermal coatings generate under the driving of 3.6V power supplys makes on blade
The ice sheet contacted with electro-thermal coatings melts, and the accumulated ice on blade is removed immediately under the influence of centrifugal force.
Embodiment two：Different according to anti-/ clearing ice technology standard require, by electric-heating coatings (such as carbon fiber/acrylic acid tree
Grease coating material) segmentation be coated on the easy ice field of fixed nose of wing, built based on the electro-thermal coatings formed after solidification each other solely
/ deicing system is prevented in vertical electrical heating；If it is considered that wing matrix electrical isolation requirement, then electro-thermal coatings should build on insulating coating
On；If required to application appearance, application color is needed on electro-thermal coatings again to meet the requirements under normal circumstances
Conduct heat coating.In this way, be set to the leading edge of a wing each anti-/ deicing system can under the driving of 3-7V power supplys independent operating, it is attached
The accumulated ice in the leading edge of a wing is removed immediately.
Although being described in further detail to the present invention with reference to above-described embodiment, those skilled in the art should manage
Solution：It can still modify to the technical solution recorded in the various embodiments described above, or to which part technical characteristic into
Row equivalent replacement；And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (4)
1. it is a kind of for aircraft it is anti-/ electric-heating technology of deicing, it is characterised in that：(1) electricity is used to be used as heating energy source；(2)
Using electro-thermal coatings as electrical heating elements.
2. electric-heating technology as described in claim 1, it is characterised in that：The heat that electro-thermal coatings generate under the driving of power supply is used
In anti-/ anti-ice operation of aircraft.
3. electric-heating technology as claimed in claim 2, it is characterised in that：Electro-thermal coatings are attached by coating process by electric-heating coatings
It on matrix surface, is conductive solids.
4. electric-heating technology as claimed in claim 2, it is characterised in that：Electro-thermal coatings are located at the surface or close of aircraft
Level in surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710248415.4A CN108725802A (en) | 2017-04-17 | 2017-04-17 | It is a kind of for aircraft it is anti-/ electric-heating technology of deicing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710248415.4A CN108725802A (en) | 2017-04-17 | 2017-04-17 | It is a kind of for aircraft it is anti-/ electric-heating technology of deicing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108725802A true CN108725802A (en) | 2018-11-02 |
Family
ID=63923807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710248415.4A Pending CN108725802A (en) | 2017-04-17 | 2017-04-17 | It is a kind of for aircraft it is anti-/ electric-heating technology of deicing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108725802A (en) |
-
2017
- 2017-04-17 CN CN201710248415.4A patent/CN108725802A/en active Pending
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181102 |