CN104875894A - Dielectric barrier discharge plasma anti-icing device and method - Google Patents
Dielectric barrier discharge plasma anti-icing device and method Download PDFInfo
- Publication number
- CN104875894A CN104875894A CN201510277732.XA CN201510277732A CN104875894A CN 104875894 A CN104875894 A CN 104875894A CN 201510277732 A CN201510277732 A CN 201510277732A CN 104875894 A CN104875894 A CN 104875894A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- insulating barrier
- plasma
- electrical source
- electrode
- 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
Abstract
The invention discloses a dielectric barrier discharge plasma anti-icing device and method. A plurality of layers of polyimide adhesive tape are overlapped and pasted to serve as an insulation layer. Upper electrodes and lower electrodes are pasted along the two side faces of the insulation layer in a staggered mode. The upper electrodes are connected in parallel to be connected with a positive electrode of a plasma power source. The lower electrodes are connected in parallel to be connected with a negative electrode of the plasma power source. The insulation layer is fixed into a groove in the surface of an aircraft skin, and efficient anti-icing of the surface of an aircraft is achieved. Due to the fact that the thickness of the electrodes and the thickness of the insulation layer are very small, the effect of the electrodes and the insulation layer on the aerodynamic performance of the aircraft can be ignored. The dielectric barrier discharge plasma anti-icing device is simple in structure, and the electrodes can be flexibly distributed according to the different geometrical shapes of the frozen positions of the aircraft. When the voltage of the plasma power source is adjusted to 70 V and the current strength ranges from 1.5 A to 2.5 A, the voltage actually loaded to the electrodes can reach 10 KV or more, the responding time is short, the anti-icing effect is good, the implement method is convenient to implement and easy to achieve and has good application prospects, and no pollution exists.
Description
Technical field
The present invention relates to for the anti-freeze apparatus and method of aircraft surface, specifically, relate to a kind of applicating medium barrier discharge plasma deicing and method.
Technical background
Aircraft is when passing through in the cloud layer containing super-cooling waterdrop, the parts windward of aircraft, if windshield, wing, rotor, vertical fin, driving engine etc. are when without all there will be icing phenomenon when anti-ice removal system, and aircraft key position freezes and becomes the large hidden danger of one in flight safety.Aircraft key position freezes and understands the aerodynamic configuration of change of flight device, has a strong impact on the aerodynamic characteristic of aircraft, and the road-holding property of aircraft and stability are worsened, the resistance of aircraft can be made to increase as the leading edge of a wing freezes, lift reduces, and stalling incidence reduces, and maneuvering performance declines; Driving engine freezes directly can affect the normal operation of driving engine, and engine efficiency is reduced greatly; Windshield freezes and reduces its diaphaneity, makes range estimation flight become difficulty, causes certain potential safety hazard when take-off and landing; In addition, some thermometrics, pressure measurement sensing head can cause instrument display distortion, even mislead the driving of aviator after freezing.
At present, main anti-icing technology has electro-thermal anti-ice, and gas heat is anti-icing, the anti-icing method of chemical liquids.Electro-thermal anti-ice be by electric energy conversion be heat energy to the anti-icing technology of the heating power heating aircraft outside face, be generally divided into resistance wire type and conductive film type two kinds, the method reliability is higher, lightweight, is easy to realize, but its to have response comparatively slow, consume energy higher shortcoming.Gas heat is anti-icing is the anti-icing technology of heating power utilizing the mode adding hot air to heat aircraft surface, and generally using engine bleed as thermal source, under the method square one, energy consuming ratio electro thermal ice protection system is high 2 ~ 3 times.Chemical liquids is anti-icing is spray anti-freeze fluid to aircraft surface, mix with the subcooled water impinging upon surface, mixed liquor solidfying point is made to reach the anti-icing technology of one of anti-icing object lower than aircraft surface temperature, the method power consumption is low, system is simple, but aircraft load can be increased, the restriction flight time, and certain pollution can be produced to environment.
Summary of the invention
In order to avoid the deficiency that prior art exists, overcome its anti-freeze technology application low-response, consume energy problem that is high, contaminated environment, the present invention proposes a kind of applicating medium barrier discharge plasma deicing and method.
The technical solution adopted for the present invention to solve the technical problems is: applicating medium barrier discharge plasma deicing, comprise plasma electrical source, characterized by further comprising top electrode, bottom electrode, insulating barrier, described insulating barrier adopts the superposition of multilayer polyimide adhesive tape bonding, and insulating barrier is fixed on aircraft and easily freezes in the skin-surface groove of position; Described top electrode is interspersed bonding with described bottom electrode along insulating barrier two sides, top electrode parallel connection is connected with plasma electrical source positive pole by wire, bottom electrode parallel connection is connected with plasma electrical source negative pole by wire, described top electrode and described bottom electrode are strip shape, thickness is 0.035mm, top electrode width is 1 ~ 5mm, and bottom electrode width is 8 ~ 15mm.
Utilize the method that described applicating medium barrier discharge plasma is anti-freeze, it is characterized in that comprising the following steps:
Step 1. determines electrode material and insulating barrier size; Select sheet copper as electrode material, insulating barrier choose thickness be 0.076mm Kapton Tape superposition bonding, superimposed layer is greater than 4 layers to ensure that insulating barrier is not breakdown, employing insulating gel as lining cement;
After step 2. is bonding with insulating barrier by top electrode, bottom electrode, is fixedly bonded to aircraft and easily freezes in the skin-surface groove of position, and smooth with aircraft skin smooth surface, guarantee between insulating barrier and bottom electrode without air filled cavity;
The parallel connection of step 3. top electrode is connected by wire with plasma electrical source positive pole, and bottom electrode parallel connection is connected by wire with plasma electrical source negative pole;
Step 4. when the flight environment of vehicle that aircraft encounter easily freezes, open plasma source switch, regulating power source voltage is to 70V, intensity of current is 1.5 ~ 2.5A, regulate plasma electrical source output frequency to make outgoing current reach maximum, top electrode starts electric discharge, produces heating region around;
Step 5. keeps plasma electrical source open mode until aircraft leaves the flight environment of vehicle easily frozen;
Step 6., when aircraft flies away from easy icing flight environment, closes plasma electrical source.
Beneficial effect
A kind of applicating medium barrier discharge plasma deicing that the present invention proposes and method, adopt multilayer polyimide adhesive tape bonding as insulating barrier, top electrode and bottom electrode distribute along insulating barrier two sides interleaved and paste, top electrode parallel connection is connected with plasma electrical source positive pole by wire, bottom electrode parallel connection is connected with plasma electrical source negative pole by wire, insulating barrier is fixed in aircraft skin surface groove, and form one with aircraft skin surface, realize the efficiently anti-icing of aircraft surface.Because the thickness of electrode and insulating barrier is minimum, can ignore the impact of the aeroperformance of aircraft.Applicating medium barrier discharge plasma deicing structure is simple, and electrode arrangements can be arranged flexibly according to the difference of the geometric configuration of aircraft ice forming locations.When plasma electrical source voltage-regulation is to 70V, intensity of current is 1.5 ~ 2.5A, and actual energy consumption is lower, and on electrode, the voltage of actual loaded can reach more than 10KV, and response time is fast, and the heating region electric field intensity of local is higher, anti-icing respond well.
The anti-freeze technology of applicating medium barrier discharge plasma compare existing anti-icing technology have structure simply, do not affect flight vehicle aerodynamic performance, fast response time, anti-icing successful, consume energy low; Implementation method is convenient, pollution-free and be easy to realize advantage, have a good application prospect.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of applicating medium barrier discharge plasma deicing of the present invention and method are described in further detail.
Fig. 1 is applicating medium barrier discharge plasma deicing schematic diagram of the present invention.
Fig. 2 is electrode arrangements of the present invention and connection line schematic diagram.
Fig. 3 is electrode arrangements partial enlarged drawing of the present invention.
In figure:
1. plasma electrical source 2. top electrode 3. bottom electrode 4. insulating barrier 5. aircraft skin 6. heating region
Detailed description of the invention
The present embodiment is a kind of applicating medium barrier discharge plasma deicing and method.
Consult Fig. 1, Fig. 2, Fig. 3, applicating medium barrier discharge plasma deicing is made up of plasma electrical source 1 and top electrode 2, bottom electrode 3, insulating barrier 4, it is bonding that insulating barrier 4 adopts multilayer polyimide adhesive tape to superpose, and insulating barrier 4 is fixed on aircraft and easily freezes in the skin-surface groove of position.Top electrode 2 is interspersed bonding with bottom electrode 3 along insulating barrier 4 two sides, and the positive pole of plasma electrical source 1 is connected by wire with the top electrode 2 of arranged in parallel, and the negative pole of plasma electrical source 1 is connected by wire with the bottom electrode 3 of arranged in parallel.Top electrode and bottom electrode are strip shape, and thickness is 0.035mm, and the width of top electrode is 1 ~ 5mm, and bottom electrode width is 8 ~ 15mm.When containing a certain amount of subcooled water in air, open plasma power supply 1, forms territory, plasma glow zone above electrode, and super-cooling waterdrop is broken after striking object plane forms moisture film, moisture film is taken away aura region under action of plasma, reaches anti-freeze object.
Utilize the method that described applicating medium barrier discharge plasma is anti-freeze, it is characterized in that comprising the following steps:
Step one, determines electrode material and insulating barrier size;
Choose sheet copper as electrode material; Insulating barrier choose thickness be 0.076mm Kapton Tape superposition bonding, superimposed layer is greater than 4 layers to ensure that insulating barrier is not breakdown; Adopt insulating gel as lining cement;
Step 2, after top electrode 2, bottom electrode 3 is bonding with insulating barrier 4, be fixedly bonded to aircraft and easily freeze in the skin-surface groove of position, and smooth with aircraft skin 5 smooth surface, guarantees between insulating barrier 4 and bottom electrode 3 without air filled cavity;
Step 3, top electrode 2 is in parallel and be connected by wire with the high-voltage output terminal mouth of plasma electrical source 1, and bottom electrode 3 is in parallel and be connected by wire with the low-voltage output port of plasma electrical source 1;
Step 4, when aircraft meets with icing flight environment of vehicle aloft, open plasma power supply 1 switch, regulating power source voltage is to 70V, and intensity of current is 1.5 ~ 2.5A, regulates plasma electrical source output frequency to make outgoing current reach maximum, electrode discharge, makes to produce heating region 6 around; Super-cooling waterdrop in air impinges upon heating region 6, can not undergo phase transition and freeze and taken away this region under action of plasma.
Step 5, keeps plasma electrical source open mode until aircraft flies away from the flight environment of vehicle easily frozen;
Step 6, when aircraft flies away from easy icing flight environment, closes plasma electrical source.
Claims (2)
1. an applicating medium barrier discharge plasma deicing, comprise plasma electrical source, it is characterized in that: also comprise top electrode, bottom electrode, insulating barrier, described insulating barrier adopts the superposition of multilayer polyimide adhesive tape bonding, and insulating barrier is fixed on aircraft and easily freezes in the skin-surface groove of position; Described top electrode is interspersed bonding with described bottom electrode along insulating barrier two sides, top electrode parallel connection is connected with plasma electrical source positive pole by wire, bottom electrode parallel connection is connected with plasma electrical source negative pole by wire, described top electrode and described bottom electrode are strip shape, thickness is 0.035mm, top electrode width is 1 ~ 5mm, and bottom electrode width is 8 ~ 15mm.
2. utilize the method that the applicating medium barrier discharge plasma described in claim 1 is anti-freeze, it is characterized in that comprising the following steps:
Step 1. determines electrode material and insulating barrier size; Select sheet copper as electrode material, insulating barrier choose thickness be 0.076mm Kapton Tape superposition bonding, superimposed layer is greater than 4 layers to ensure that insulating barrier is not breakdown, employing insulating gel as lining cement;
After step 2. is bonding with insulating barrier by top electrode, bottom electrode, is fixedly bonded to aircraft and easily freezes in the skin-surface groove of position, and smooth with aircraft skin smooth surface, guarantee between insulating barrier and bottom electrode without air filled cavity;
The parallel connection of step 3. top electrode is connected by wire with plasma electrical source positive pole, and bottom electrode parallel connection is connected by wire with plasma electrical source negative pole;
Step 4. when the flight environment of vehicle that aircraft encounter easily freezes, open plasma source switch, regulating power source voltage is to 70V, intensity of current is 1.5 ~ 2.5A, regulate plasma electrical source output frequency to make outgoing current reach maximum, top electrode starts electric discharge, produces heating region around;
Step 5. keeps plasma electrical source open mode until aircraft leaves the flight environment of vehicle easily frozen;
Step 6., when aircraft flies away from easy icing flight environment, closes plasma electrical source.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510277732.XA CN104875894A (en) | 2015-05-27 | 2015-05-27 | Dielectric barrier discharge plasma anti-icing device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510277732.XA CN104875894A (en) | 2015-05-27 | 2015-05-27 | Dielectric barrier discharge plasma anti-icing device and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104875894A true CN104875894A (en) | 2015-09-02 |
Family
ID=53943636
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510277732.XA Pending CN104875894A (en) | 2015-05-27 | 2015-05-27 | Dielectric barrier discharge plasma anti-icing device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104875894A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN109573056A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Ice detection and application based on the excitation of radio frequency sharp discharge plasma |
| CN109573055A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Icing sensing and anti-deicing integrating device and its application method based on plasma |
| CN110481792A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of novel plasma ice shape regulation device, method and anti-freeze type aircraft |
| CN111942594A (en) * | 2019-05-14 | 2020-11-17 | 空中客车西班牙有限责任公司 | Aircraft, method for detecting the presence of ice and method for improving aerodynamics |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1017580B1 (en) * | 1997-09-22 | 2004-08-04 | Northcoast Technologies | De-ice and anti-ice system and method for aircraft surfaces |
| WO2007106863A2 (en) * | 2006-03-14 | 2007-09-20 | University Of Notre Dame Du Lac | Methods and apparatus for reducing noise via a plasma fairing |
| CN101511146A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Zero mass jet flow exciter of medium countercheck discharging plasma |
| CN101666343A (en) * | 2008-09-03 | 2010-03-10 | 中国科学院工程热物理研究所 | Control system and control method for plasma excitation for cascade internal flow |
| CN102595758A (en) * | 2011-01-12 | 2012-07-18 | 中国科学院工程热物理研究所 | Dielectric barrier discharge (DBD) plasma trailing edge jetting device and method |
| CN102991666A (en) * | 2012-11-26 | 2013-03-27 | 中国商用飞机有限责任公司 | Laminated plate aircraft skin with flow control and deicing prevention functions |
-
2015
- 2015-05-27 CN CN201510277732.XA patent/CN104875894A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1017580B1 (en) * | 1997-09-22 | 2004-08-04 | Northcoast Technologies | De-ice and anti-ice system and method for aircraft surfaces |
| WO2007106863A2 (en) * | 2006-03-14 | 2007-09-20 | University Of Notre Dame Du Lac | Methods and apparatus for reducing noise via a plasma fairing |
| CN101666343A (en) * | 2008-09-03 | 2010-03-10 | 中国科学院工程热物理研究所 | Control system and control method for plasma excitation for cascade internal flow |
| CN101511146A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Zero mass jet flow exciter of medium countercheck discharging plasma |
| CN102595758A (en) * | 2011-01-12 | 2012-07-18 | 中国科学院工程热物理研究所 | Dielectric barrier discharge (DBD) plasma trailing edge jetting device and method |
| CN102991666A (en) * | 2012-11-26 | 2013-03-27 | 中国商用飞机有限责任公司 | Laminated plate aircraft skin with flow control and deicing prevention functions |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN109573056A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Ice detection and application based on the excitation of radio frequency sharp discharge plasma |
| CN109573055A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Icing sensing and anti-deicing integrating device and its application method based on plasma |
| CN109573055B (en) * | 2018-11-24 | 2020-08-11 | 中国人民解放军空军工程大学 | Application method of plasma-based icing sensing and deicing prevention integrated device |
| CN111942594A (en) * | 2019-05-14 | 2020-11-17 | 空中客车西班牙有限责任公司 | Aircraft, method for detecting the presence of ice and method for improving aerodynamics |
| CN110481792A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of novel plasma ice shape regulation device, method and anti-freeze type aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104890881A (en) | Icing removing device and method of dielectric barrier discharge plasma | |
| CN104875894A (en) | Dielectric barrier discharge plasma anti-icing device and method | |
| CN108016622B (en) | A kind of active aircraft anti-icing method and device | |
| CN109334998A (en) | A kind of gradient distribution formula plasma de-icing device and method | |
| CN107889335A (en) | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method | |
| CN109665093A (en) | A kind of aerofoil profile delaying flow separation and the driver being placed in aerofoil profile | |
| CN110510102B (en) | Attachable self-resistance heating/super-hydrophobic integrated gradient film material | |
| CN109862637A (en) | A kind of anti-deicing electric heating device and preparation method with graphene-carbon nano tube composite material | |
| CN103661929A (en) | Plasma unmanned aerial vehicle | |
| CN205265933U (en) | Multilayer structure's anti -icing component of electrical heating | |
| CN105000171A (en) | Low-speed stall control device for flying wing-configured aircraft and control method thereof | |
| CN201238183Y (en) | Deicing mechanism by electrical pulse method for power transmission line | |
| CN110481792A (en) | A kind of novel plasma ice shape regulation device, method and anti-freeze type aircraft | |
| CN204887661U (en) | Insulating medium's plasma driver device is regarded as with pottery | |
| CN112757717A (en) | Directional heat conduction electric heating device and preparation method | |
| CN203104936U (en) | Plasma exciter using quartz glass as insulating medium | |
| CN113148183A (en) | Plasma hot knife and hydrophobic material combined type deicing device and application | |
| Xie et al. | Multipurpose distributed dielectric-barrier-discharge plasma actuation: Icing sensing, anti-icing, and flow control in one | |
| CN203497174U (en) | Flexible strip-shaped plasma exciter | |
| CN106837682A (en) | A kind of wind turbine blade with lightning protection deicing function | |
| CN109319169A (en) | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall | |
| CN109413831B (en) | Plasma synthesis jet generator capable of controlling temperature in cavity and application thereof | |
| CN114104299B (en) | Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating | |
| CN206681920U (en) | A kind of fan blade of wind generating set that can prevent from freezing | |
| CN112572808B (en) | Double-layer anti-icing and electric heating structure and wing adopting same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Xu Shuangyan Inventor after: Cai Jinsheng Inventor after: Tian Yongqiang Inventor after: Meng Xuanshi Inventor before: Cai Jinsheng Inventor before: Xu Shuangyan Inventor before: Tian Yongqiang Inventor before: Meng Xuanshi |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: CAI JINSHENG XU SHUANGYAN TIAN YONGQIANG MENG XUANSHI TO: XU SHUANGYAN CAI JINSHENG TIAN YONGQIANG MENG XUANSHI |
|
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150902 |