A kind of applicating medium barrier discharge plasma deicing and method
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.