CN108545197A - The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma - Google Patents
The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma Download PDFInfo
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 7
- 229910052802 copper Inorganic materials 0.000 claims description 7
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- 229910001053 Nickel-zinc ferrite Inorganic materials 0.000 claims description 5
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- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 3
- 229910001289 Manganese-zinc ferrite Inorganic materials 0.000 claims description 3
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- 238000010438 heat treatment Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000005611 electricity Effects 0.000 description 4
- 238000007710 freezing Methods 0.000 description 3
- 230000008014 freezing Effects 0.000 description 3
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- 238000010257 thawing Methods 0.000 description 2
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Classifications
-
- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Plasma Technology (AREA)
Abstract
A kind of device for being encouraged using rf (discharge) plasma and carrying out the anti-deicing of wing, including radio-frequency power supply (101), impedance matching circuit (102), anti-deicing device (103) are provided；The output end of radio-frequency power supply (101) is connected to the primary of impedance matching circuit (102), and the secondary of impedance matching circuit (102) is connected to the anode of anti-deicing device (103)；Anti- deicing device (103) is for generating plasma (104)；A kind of method for being encouraged using rf (discharge) plasma and carrying out the anti-deicing of wing is also provided.Apparatus and method of the present invention Mechanical Reliability is strong, movement-less part, and can be applied to air intake duct, tail-rotor, antenna house etc. has the control occasion of similar anti-deicing demand for control.Apparatus and method of the present invention also has many advantages, such as that efficiency of heating surface height, stable discharge, power regulation are convenient, it is contemplated that will be with a wide range of applications in terms of the anti-deicing of aircraft.
Description
Technical field
The present invention relates to plasma discharging teclmiques, and in particular to a kind of to encourage carry out machine using rf (discharge) plasma
The device and method of the anti-deicing of the wing.
Background technology
For aircraft under the conditions of icing meteorology when flight, the super-cooling waterdrop in air hits aircraft surface, easily wing,
The parts surfaces such as tail-rotor, air intake duct, antenna house freeze.This will increase the weight of aircraft, and destroy the aerodynamic configuration of aircraft,
Its aerodynamic characteristics is influenced, flight safety is seriously affected, can lead to fatal crass under extreme condition.Therefore, it is necessary to fly
Anti- deicing system is installed on device, icing accident is reduced and occurs, ensure flight safety.
Commonly the anti-de-icing method of wing includes：Chemical formula, mechanical, electrothermal etc..The anti-de-icing method pollution of chemical formula
Seriously, reliability is not high；Mechanical anti-deicing can then cause additional drag, and being only capable of deicing cannot be anti-icing.At present in aircraft
On mainly using the anti-de-icing method of electrothermal.However, there are high energy consumptions, complicated etc. to ask for the anti-de-icing method of electrothermal
Topic.In recent years, using plasma encourages the research for carrying out anti-deicing to start to rise.
Arc discharge, radio frequency discharge, corona discharge, nanosecond pulse dielectric barrier discharge etc. can be used for generating plasma
Body encourages.Compared with other discharge modes, radio frequency discharge has the technical advantages such as the efficiency of heating surface is high, power regulation facilitates, and is one
The very promising anti-deicing energisation mode of kind.
Rf (discharge) plasma encourages the basic principle of anti-deicing to be：Plasma is generated by radio frequency discharge means,
Plasma generation process is acted on along with Wen Sheng and pressure liter, forms rf (discharge) plasma excitation, plasma excitation
Wen Sheng and pressure liter act on the parts surfaces such as wing, air intake duct, can prevent the components such as wing, air intake duct freeze, or
Remove the icing of these parts surfaces.Domestic and international research institution not yet uses rf (discharge) plasma excitation to carry out aircraft table
The research of the anti-deicing in face.
Invention content
The present invention proposes a kind of device for being encouraged using rf (discharge) plasma and carrying out the anti-deicing of wing, including radio frequency electrical
Source 101, impedance matching circuit 102, anti-deicing device 103；The output end of wherein radio-frequency power supply 101 is connected to impedance matching circuit
102 primary, the secondary of impedance matching circuit 102 are connected to the anode of anti-deicing device 103, the negative terminal of anti-deicing device 103
Ground connection.Anti- deicing device 103 is for generating plasma 104；Wherein
Radio-frequency power supply 101 is made of signal generating circuit and power amplification circuit, and working frequency is continuously adjustable, radio-frequency power supply
101 operational frequency bandwidth is 10kHz~10MHz；The output signal power of radio-frequency power supply 101 is continuously adjustable, power bracket
For 0~1500W；
Impedance matching circuit 102 is made of high frequency transformation coil 201 and capacitance 202, and the anode of radio-frequency power supply 101 passes through electricity
Hold and 202 be connected with the anode of the primary coil of high frequency transformation coil 201, the negative terminal of the primary coil of high frequency transformation coil 201 and
The negative terminal of radio-frequency power supply 101 is connected；Iron-core coil material can be selected from nickel-zinc ferrite or manganese-zinc ferrite, magnetic conductivity 500-
1500, coil ratio 1: 3-1: 10；202 value of capacitance ranging from 10pF-50pF；The actual functional capability of impedance matching circuit 102
It is not limited in reducing the feedback power loss of radio-frequency power supply 101, moreover it can be used to increase the load at 101 electrode both ends of radio-frequency power supply
Voltage, to realize the radio frequency discharge under different air pressures；The anode and radio-frequency power supply of the secondary coil of impedance matching circuit 102
101 anode is connected, the negativing ending grounding of the secondary coil of impedance matching circuit 102；
Anti- deicing device 103 is installed in the groove of metal or composite machine wing surface, is spread from wing root to wing tip,
Through entire or most of wing in spanwise, installation rear defence deicing device 103 must be concordant with wing adjacent part, ensures
The smooth no protrusion of aerofoil surface；Anti- deicing device 103 is one end open, can coat the upper and lower surface at one edge of wing
The shape of substantially clip firmly, therefore, it is necessary to the upper and lower surfaces at one edge of wing to form groove, which can be embedded in anti-
Deicing device 103.
In one embodiment of the invention, the operational frequency bandwidth of radio-frequency power supply 101 is 2kHz~6MHz；Radio-frequency power supply
101 output signal power ranging from 0~500W.
In one particular embodiment of the present invention, the working frequency of radio-frequency power supply 101 is 1.20MHz；Radio-frequency power supply 101
Output signal power be 300W.
In one particular embodiment of the present invention, the preferred material of 201 iron core of high frequency transformation coil is nickel-zinc iron oxygen
Body, preferably magnetic conductivity are 200；The preferred turn ratio of coil is 1: 5, and the preferred value of capacitance 202 is 20pF.
Anti- deicing device 103 is made of interior insulation/thermal insulation layer 301 and dielectric barrier discharge driver 302；
Interior insulation/thermal insulation layer 301 is rectangular tablet, length 100mm-3000mm, is equal to or slightly shorter than wing
Length, width 100mm-1000mm, the about half of wing chord length, thickness 2mm-10mm；The material of interior insulation/thermal insulation layer 301
Material selection mica or polyimides；
Dielectric barrier discharge driver 302 is made of insulation medium board 401, pellet electrode 402 and strip shaped electric poles 403；Absolutely
Edge dielectric-slab 401 is rectangular tablet, and length 100mm-3000mm, is equal to or the length of slightly shorter than wing, width are
100mm-1000mm, the about half of wing chord length, thickness 0.2mm-10mm；The material of insulation medium board 401 is sub- using polyamides
Amine or ceramic matric composite；
Pellet electrode 402 is rectangular thin slice, and length, width are equal with insulation medium board 401, length, width point
Not Wei 100mm-3000mm, 100mm-1000mm, thickness be 10 μm -100 μm；Pellet electrode 402 is laid in insulation medium board 401
Lower surface, edge is concordant with insulation medium board 401, and pellet electrode 402 is completely covered by insulation medium board 401；Pellet electrode
402 material uses copper, copper tin plating or tungsten nickel plating；
Strip shaped electric poles 403 are laid in the upper surface of insulation medium board 401, are arranged to pectination, one open up to electrode arrangement in
Near the leading edge of a wing, it is 80mm-2800mm to open up to electrode length；Remaining a plurality of tangential electrode is opened up along wing to being uniformly distributed, phase
Spacing between adjacent tangential electrode is 10mm-100mm, and tangential electrode strip number ranging from 3-30 items, tangential electrode length is 80mm-
The material of 960mm strip shaped electric poles 403 uses copper, copper tin plating or tungsten nickel plating；It is 1mm- to open up to the width of electrode and tangential electrode
10mm, thickness are 10 μm -100 μm.
In one particular embodiment of the present invention, the length of interior insulation/thermal insulation layer 301 is the length of wing, and width is
The half of wing chord length, thickness 5mm；The material selection mica of interior insulation/thermal insulation layer 301.
In one particular embodiment of the present invention, the length of insulation medium board 401 is the length of wing, and width is wing
The half of chord length, thickness 0.35mm, using ceramic matric composite.
In one particular embodiment of the present invention, the length of pellet electrode 402 is 220mm, width 150mm, thickness
It it is 35 μm, selected materials are tungsten nickel plating.
In one particular embodiment of the present invention, strip shaped electric poles 403 use tungsten nickel plating, open up to electrode and tangential electrode
Width is 2mm, and thickness is 35 μm；It is 180mm to open up to electrode length；Tangential electrode is 5, length 130mm, the 1st and the 5th
For root respectively apart from the left and right edge same distance of wing, the spacing of adjacent tangential electrode is 35mm.
A kind of method for being encouraged using rf (discharge) plasma and carrying out the anti-deicing of wing is also provided, is included the following steps：
(a) apply radio-frequency voltage, voltage range 500V-3000V at the electrode both ends of anti-deicing device 103, adjustment is penetrated
The working frequency of frequency power 101 makes radio-frequency power supply 101, impedance matching circuit 102, anti-deicing device 103 be in resonant condition；
(b) plasma 104, plasma generation process are generated on anti-deicing device 103 using radio frequency discharge mode
It is acted on along with Wen Sheng and pressure liter, forms rf (discharge) plasma excitation, the Wen Sheng and pressure of plasma excitation, which rise, to be made
For wing, the ice that aerofoil surface has been formed that freezes or remove is prevented；
(c) output power for changing radio-frequency power supply 101, studies its influence to anti-deicing effect, selects optimal output work
Rate, wherein it is 0-500W that can apply power bracket, and preferred scope output power is 300W；
(d) working frequency for changing radio-frequency power supply 101, studies its influence to anti-deicing effect, selects optimal work frequency
Rate, wherein the optional range of working frequency is 100kHz~6MHz；
(e) pulse width and the pulse period for changing radio-frequency power supply 101, that is, change the duty ratio of anti-deicing device, to
The presence of aerofoil surface overflow water is reduced, the generation of ice tumor is reduced；Wherein, the optional adjustable range of pulse width is 1-500 μ s,
The optional adjustable range of pulse period is 1-50ms.
In one particular embodiment of the present invention, in step (a), apply at the electrode both ends of anti-deicing device 103
Radio-frequency voltage 2000V；The step-up ratio of impedance matching circuit 102 is 1: 4, and resonant frequency is about 1.20MHz.
In one particular embodiment of the present invention, in step (c), the output power for changing radio-frequency power supply 101 is
300W。
In one particular embodiment of the present invention, in step (d), the working frequency for changing radio-frequency power supply 101 is
1.20MHz。
In one particular embodiment of the present invention, in step (e), by the pulse width of radio-frequency power supply 101 and pulse
Period changes into 500 μ s and 5ms respectively.
The method that the present invention carries out the anti-deicing of wing using rf (discharge) plasma excitation, passes through radio frequency discharge plasma
Wen Sheng and pressure the liter effect that body generates, prevent the water droplet for striking wing cover surface from freezing；Evaporate wing cover table
The water that face is collected into；Melt the frozen ice of wing skin-surface, destroys the adhesion strength between ice sheet and covering, make the ice cube of thawing
It is blown away or gets rid of away under the action of aerodynamic force or centrifugal force；To achieve the purpose that the anti-deicing of wing.This method machinery is reliable
Property strong, movement-less part, in addition to wing, applying also for air intake duct, tail-rotor, antenna house etc. has the portion of similar anti-deicing demand
Position.In addition, this method has many advantages, such as that efficiency of heating surface height, stable discharge, power regulation are convenient, it is contemplated that will be in the anti-deicing of aircraft
Aspect is with a wide range of applications.
Description of the drawings
Fig. 1 is the device composition schematic diagram that the present invention carries out the anti-deicing of wing using rf (discharge) plasma excitation；
Fig. 2 is the structural schematic diagram of impedance matching circuit 102；
Fig. 3 is arranged on the structural schematic diagram of the anti-deicing device 103 at the leading edge of a wing；
Fig. 4 is the electrode arrangement schematic diagram of dielectric barrier discharge driver 302；
Fig. 5 is the design sketch that anti-deicing is carried out using rf (discharge) plasma excitation, and wherein Fig. 5 (a) shows not apply
The case where the case where plasma excitation, Fig. 5 (b) is shown to apply after plasma excitation 2min.
Specific implementation mode
In conjunction with attached drawing, the present invention is described in further detail.
The basic principle for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma, is to utilize radio frequency discharge plasma
The fuel factor and aerodynamic effect of body, come the ice for preventing aerofoil surface from freezing or removal aerofoil surface has been formed.
The schematic device for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma as shown in Figure 1, including radio frequency
Power supply 101, impedance matching circuit 102, anti-deicing device 103；The output end of wherein radio-frequency power supply 101 is connected to impedance matching electricity
The primary on road 102, the secondary of impedance matching circuit 102 are connected to the anode of anti-deicing device 103, and anti-deicing device 103 is born
End ground connection.Anti- deicing device 103 is for generating plasma 104.
Radio-frequency power supply 101 is made of signal generating circuit and power amplification circuit, and working frequency is continuously adjustable, in the present invention
One embodiment in, the operational frequency bandwidth of radio-frequency power supply 101 is 2kHz~6MHz, but is not limited to the bandwidth range,
Other working frequencies, such as 10kHz~10MHz can be used in other embodiments, preferred working frequency is 1.20MHz.Radio frequency
The output signal power of power supply 101 is continuously adjustable, and in one embodiment of the invention, power bracket is 0~500W, but simultaneously
It is not limited to the power bracket, can use other output power models according to conditions such as air pressure, electrode gaps in other embodiments
It encloses, such as 0~1500W, the preferred output power of radio-frequency power supply 101 is 300W；Working frequency, the output work of radio-frequency power supply 101
The parameters such as rate can in real time be adjusted by serial ports or other means.In one particular embodiment of the present invention, radio-frequency power supply
101 can be used the AG1024 type radio-frequency power amplifiers of T＆C companies of the U.S., and concrete structure is no longer described in detail.
In one embodiment of the invention, as shown in Fig. 2, impedance matching circuit 102 is by high frequency transformation coil 201 and electricity
Holding 202 compositions, the anode of radio-frequency power supply 101 is connected by capacitance 202 with the anode of the primary coil of high frequency transformation coil 201,
The negative terminal of the primary coil of high frequency transformation coil 201 is connected with the negative terminal of radio-frequency power supply 101.201 shape of high frequency transformation coil can
Select cylindricality, I-shaped or hat shape, the optional nickel-zinc ferrite of iron-core coil material or manganese-zinc ferrite, magnetic conductivity 500-
1500, coil ratio 1: 3-1: 10；202 value of capacitance ranging from 10pF-50pF.The actual functional capability of impedance matching circuit 102
It is not limited in reducing the feedback power loss of radio-frequency power supply 101, moreover it can be used to increase the load at 101 electrode both ends of radio-frequency power supply
Voltage, to realize the radio frequency discharge under different air pressures.In Fig. 2, the secondary coil (coil on the right) of impedance matching circuit 102
Anode be connected with the anode of radio-frequency power supply 101, the negativing ending grounding of the secondary coil of impedance matching circuit 102.Its medium-high frequency becomes
The preferred material of 201 iron core of crimping circle is nickel-zinc ferrite, and preferably magnetic conductivity is 200；The preferred turn ratio of coil is 1: 5, electricity
The preferred value for holding 202 is 20pF.
Anti- deicing device 103 is core of the invention component, and anti-deicing device 103 is mounted on metal or composite machine
In the groove of wing surface, in order to reach good deicing effect, anti-deicing device 103 is generally spread from wing root to wing tip, in the wing
Zhan Fang extends upward through entire wing (can certainly suitably shorten length), and installation rear defence deicing device 103 must be with wing phase
Adjacent flush with portions ensures the smooth no protrusion of aerofoil surface, to not influence the aerodynamic characteristic of wing.Fig. 1 and illustrated in fig. 3 anti-
Deicing device 103 be one end open, the shape for the substantially clip that the upper and lower surface at one edge of wing can be enveloped, because
This needs the upper and lower surface at one edge of wing to form groove, which can be embedded in anti-deicing device 103.In practical operation
In, it can be directly attached on wing with the anti-deicing device 103 of monoblock.
As shown in figure 3, anti-deicing device 103 is made of interior insulation/thermal insulation layer 301 and dielectric barrier discharge driver 302.
Interior insulation/thermal insulation layer 301 is rectangular tablet, and length is that 100mm-3000mm (is equal to or slightly shorter than wing
Length), width is 100mm-1000mm (half for being approximately equal to wing chord length), thickness 2mm-10mm；Interior insulation/thermal insulation layer 301
Material selection mica, polyimides etc..Wherein the preferred length of interior insulation/thermal insulation layer 301 is the length of wing, such as
220mm, width are the half of wing chord length, such as 150mm, thickness 5mm；The preferred material of interior insulation/thermal insulation layer 301 selects
Mica.
As shown in Figure 3 and Figure 4, dielectric barrier discharge driver 302 is by insulation medium board 401, pellet electrode 402 and strip
Electrode 403 is constituted.Insulation medium board 401 is rectangular tablet, and length is that 100mm-3000mm (is equal to or slightly shorter than wing
Length), width is 100mm-1000mm (half for being approximately equal to wing chord length), thickness 0.2mm-10mm；Insulation medium board 401
Material uses polyimides or ceramic matric composite.The preferred length of insulation medium board 401 is the length of wing, such as
220mm, width are the half of wing chord length, such as 150mm, thickness 0.35mm, preferentially use ceramic matric composite.
Pellet electrode 402 is rectangular thin slice, and length, width are equal with insulation medium board 401, respectively 100mm-
3000mm, 100mm-1000mm, thickness are 10 μm -100 μm；Pellet electrode 402 is laid in 401 lower surface of insulation medium board,
Edge is concordant with insulation medium board 401, and pellet electrode 402 is completely covered by insulation medium board 401；The material of pellet electrode 402
Using copper, copper is tin plating or tungsten nickel plating.The preferred length of pellet electrode 402 is 220mm, and width 150mm, thickness is 35 μm, excellent
Material selection is tungsten nickel plating.
Strip shaped electric poles 403 are laid in the upper surface of insulation medium board 401, can be arranged to pectination, and one is opened up to electrode cloth
It is placed near the leading edge of a wing, it is 80mm-2800mm to open up to electrode length；Remaining a plurality of tangential electrode is opened up along wing to uniform point
Cloth, the spacing between adjacent tangential electrode are 10mm-100mm, tangential electrode strip number ranging from 3-30 items, and tangential electrode length is
80mm-960mm.The material of strip shaped electric poles 403 uses copper, copper tin plating or tungsten nickel plating.Strip shaped electric poles 403 preferably use tungsten nickel plating,
It is 1mm-10mm to open up to the width of electrode and tangential electrode, and thickness is 10 μm -100 μm, preferable width 2mm, and thickness is 35 μm.
It is preferably 180mm to open up to electrode length.Tangential electrode is preferably 5, preferred length 130mm, is extended to being uniformly distributed in machine
On the wing, the 1st and the 5th respectively apart from the left and right edge same distance (such as 15mm) of wing, the spacing of adjacent tangential electrode is
35mm。
In order to which the voltage or power that are applied on anti-103 electrode of deicing device are maximum, by adjusting radio frequency electrical when experiment
The working frequency in source 101 makes radio-frequency power supply 101, impedance matching circuit 102, anti-deicing device 103 be in resonant condition.
It is including following the present invention also provides a kind of method for being encouraged using rf (discharge) plasma and carrying out the anti-deicing of wing
Step：
(a) apply radio-frequency voltage, voltage range 500V-3000V, preferred value at the electrode both ends of anti-deicing device 103
For 2000V, the working frequency of radio-frequency power supply 101 is adjusted, radio-frequency power supply 101, impedance matching circuit 102, anti-deicing device 103 are made
In resonant condition；
In one embodiment of the invention, the step-up ratio of impedance matching circuit 102 is 1: 4, and resonant frequency is about
1.20MHz。
(b) plasma 104, plasma generation process are generated on anti-deicing device 103 using radio frequency discharge mode
It is acted on along with Wen Sheng and pressure liter, forms rf (discharge) plasma excitation, the Wen Sheng and pressure of plasma excitation, which rise, to be made
For wing, the ice that aerofoil surface has been formed that freezes or remove is prevented.
(c) output power for changing radio-frequency power supply 101, studies its influence to anti-deicing effect, selects optimal output work
Rate, wherein it is 0-500W that can apply power bracket, and preferred scope output power is 300W；
(d) working frequency for changing radio-frequency power supply 101, studies its influence to anti-deicing effect, selects optimal work frequency
Rate, wherein the optional range of working frequency is 100kHz~6MHz, and preferably working frequency is 1.20MHz；
(e) pulse width and the pulse period for changing radio-frequency power supply 101, that is, change the duty ratio of anti-deicing device, to
The presence of aerofoil surface overflow water is reduced, the generation of ice tumor is reduced.Wherein, the optional adjustable range of pulse width is 1-500 μ s,
Preferred scope is that pulse width is 500 μ s, and the optional adjustable range of pulse period is 1-50ms, and the preferred pulse period is 5ms.
Fig. 5, which is shown, applies the front and back icing figure of rf (discharge) plasma excitation.Fig. 5 (a) shows not apply plasma
The case where body encourages, Fig. 5 (b) show after applying plasma excitation 2min that the part that top half generates plasma does not have
There is icing, lower half portion distance at a distance, does not generate plasma, after comparing two figures it can be found that applying excitation with the presence of ice crystal
Ice-out on wing, to play the effect of deicing.
The method that the present invention carries out the anti-deicing of wing using rf (discharge) plasma excitation, passes through radio frequency discharge plasma
The warm liter effect that body generates, prevents the water droplet for striking wing cover surface from freezing；Evaporation wing skin-surface is collected into
Water；Melt the frozen ice of wing skin-surface, destroys the adhesion strength between ice sheet and covering, make the ice cube of thawing in aerodynamic force
Or it is blown away or gets rid of away under the action of centrifugal force；To achieve the purpose that the anti-deicing of wing；This method Mechanical Reliability is strong, without fortune
Dynamic component, can be applied to air intake duct, tail-rotor, antenna house etc. has the control occasion of similar anti-deicing demand for control；In addition, the party
Method also has many advantages, such as that efficiency of heating surface height, stable discharge, power regulation are convenient, it is contemplated that will have in terms of the anti-deicing of aircraft wide
General application prospect.
Claims (14)
1. a kind of encouraging the device for carrying out the anti-deicing of wing, including radio-frequency power supply (101), impedance using rf (discharge) plasma
Match circuit (102), anti-deicing device (103)；The output end of wherein radio-frequency power supply (101) is connected to impedance matching circuit
(102) primary, the secondary of impedance matching circuit (102) are connected to the anode of anti-deicing device (103), anti-deicing device
(103) negativing ending grounding；Anti- deicing device (103) is for generating plasma (104)；Wherein
Radio-frequency power supply (101) is made of signal generating circuit and power amplification circuit, and working frequency is continuously adjustable, radio-frequency power supply
(101) operational frequency bandwidth is 10kHz~10MHz；The output signal power of radio-frequency power supply (101) is continuously adjustable, power
Ranging from 0~1500W；
Impedance matching circuit (102) is made of high frequency transformation coil (201) and capacitance (202), and the anode of radio-frequency power supply (101) is logical
It crosses capacitance (202) with the anode of the primary coil of high frequency transformation coil (201) to be connected, the primary line of high frequency transformation coil (201)
The negative terminal of circle is connected with the negative terminal of radio-frequency power supply (101)；Iron-core coil material can be selected from nickel-zinc ferrite or manganese-zinc ferrite,
Magnetic conductivity is 500-1500, coil ratio 1: 3-1: 10；Capacitance (202) value ranging from 10pF-50pF；Impedance matching circuit
(102) actual functional capability is not limited in reducing the feedback power loss of radio-frequency power supply (101), moreover it can be used to increase radio-frequency power supply
(101) on-load voltage at electrode both ends, to realize the radio frequency discharge under different air pressures；The secondary of impedance matching circuit (102)
The anode of coil is connected with the anode of radio-frequency power supply (101), the negativing ending grounding of the secondary coil of impedance matching circuit (102)；
Anti- deicing device (103) is installed in the groove of metal or composite machine wing surface, is spread from wing root to wing tip, in the wing
Zhan Fang extends upward through entire or most of wing, and installation rear defence deicing device (103) must be concordant with wing adjacent part, ensures
The smooth no protrusion of aerofoil surface；Anti- deicing device (103) is one end open, can wrap the upper and lower surface at one edge of wing
The shape of the substantially clip covered, therefore, it is necessary to the upper and lower surfaces at one edge of wing to form groove, which can be embedded in
Anti- deicing device (103).
2. the device of the anti-deicing of wing, wherein radio frequency are carried out using rf (discharge) plasma excitation as described in claim 1
The operational frequency bandwidth of power supply (101) is 2kHz~6MHz；Output signal power ranging from 0~500W of radio-frequency power supply (101).
3. the device of the anti-deicing of wing, wherein radio frequency are carried out using rf (discharge) plasma excitation as claimed in claim 2
The working frequency of power supply (101) is 1.20MHz；The output signal power of radio-frequency power supply (101) is 300W.
4. the device of the anti-deicing of wing, medium-high frequency are carried out using rf (discharge) plasma excitation as described in claim 1
The preferred material of transformation coil (201) iron core is nickel-zinc ferrite, and preferably magnetic conductivity is 200；The preferred turn ratio of coil is 1:
5, the preferred value of capacitance (202) is 20pF.
5. the device of the anti-deicing of wing, anti-ice removal are carried out using rf (discharge) plasma excitation as described in claim 1
Part (103) is made of interior insulation/thermal insulation layer (301) and dielectric barrier discharge driver (302)；
Interior insulation/thermal insulation layer (301) is rectangular tablet, length 100mm-3000mm, is equal to or the exhibition of slightly shorter than wing
It is long, width 100mm-1000mm, the about half of wing chord length, thickness 2mm-10mm；The material of interior insulation/thermal insulation layer (301)
Material selection mica or polyimides；
Dielectric barrier discharge driver (302) is by insulation medium board (401), pellet electrode (402) and strip shaped electric poles (403) structure
At；Insulation medium board (401) is rectangular tablet, length 100mm-3000mm, is equal to or the length of slightly shorter than wing, wide
Degree is 100mm-1000mm, the about half of wing chord length, thickness 0.2mm-10mm；The material of insulation medium board (401) uses
Polyimides or ceramic matric composite；
Pellet electrode (402) is rectangular thin slice, and length, width are equal with insulation medium board (401), length, width point
Not Wei 100mm-3000mm, 100mm-1000mm, thickness be 10 μm -100 μm；Pellet electrode (402) is laid in insulation medium board
(401) lower surface, edge is concordant with insulation medium board (401), and pellet electrode (402) is covered completely by insulation medium board (401)
Lid；The material of pellet electrode (402) uses copper, copper tin plating or tungsten nickel plating；
Strip shaped electric poles (403) are laid in the upper surface of insulation medium board (401), are arranged to pectination, one open up to electrode arrangement in
Near the leading edge of a wing, it is 80mm-2800mm to open up to electrode length；Remaining a plurality of tangential electrode is opened up along wing to being uniformly distributed, phase
Spacing between adjacent tangential electrode is 10mm-100mm, and tangential electrode strip number ranging from 3-30 items, tangential electrode length is 80mm-
960mm；The material of strip shaped electric poles (403) uses copper, copper tin plating or tungsten nickel plating；It is 1mm- to open up to the width of electrode and tangential electrode
10mm, thickness are 10 μm -100 μm.
6. the device as claimed in claim 5 for carrying out the anti-deicing of wing using rf (discharge) plasma excitation, wherein interior exhausted
The length of edge/thermal insulation layer (301) is the length of wing, and width is the half of wing chord length, thickness 5mm；Interior insulation/thermal insulation layer
(301) material selection mica.
7. the device of the anti-deicing of wing is carried out using rf (discharge) plasma excitation as claimed in claim 5, wherein insulating
The length of dielectric-slab (401) is the length of wing, and width is the half of wing chord length, and thickness 0.35mm is multiple using ceramic base
Condensation material.
8. the device of the anti-deicing of wing, wherein sheet are carried out using rf (discharge) plasma excitation as claimed in claim 5
The length of electrode (402) is 220mm, and width 150mm, thickness is 35 μm, and selected materials are tungsten nickel plating.
9. the device of the anti-deicing of wing, wherein strip are carried out using rf (discharge) plasma excitation as claimed in claim 5
Electrode (403) uses tungsten nickel plating, and it is 2mm to open up to the width of electrode and tangential electrode, and thickness is 35 μm；It opens up to electrode length and is
180mm；Tangential electrode is 5, length 130mm, the 1st and the 5th respectively apart from the left and right edge same distance of wing, phase
The spacing of adjacent tangential electrode is 35mm.
10. a kind of encouraging the method for carrying out the anti-deicing of wing using rf (discharge) plasma, include the following steps：
(a) apply radio-frequency voltage at the electrode both ends of anti-deicing device (103), voltage range 500V-3000V adjusts radio frequency
The working frequency of power supply (101) makes radio-frequency power supply (101), impedance matching circuit (102), anti-deicing device (103) be in resonance
State；
(b) plasma (104), plasma generation process are generated on anti-deicing device (103) using radio frequency discharge mode
It is acted on along with Wen Sheng and pressure liter, forms rf (discharge) plasma excitation, the Wen Sheng and pressure of plasma excitation, which rise, to be made
For wing, the ice that aerofoil surface has been formed that freezes or remove is prevented；
(c) output power for changing radio-frequency power supply (101), studies its influence to anti-deicing effect, selects optimal output power,
Wherein, it is 0-500W that can apply power bracket, and preferred scope output power is 300W；
(d) working frequency for changing radio-frequency power supply (101), studies its influence to anti-deicing effect, selects optimum working frequency,
Wherein, the optional range of working frequency is 100kHz~6MHz；
(e) pulse width and the pulse period for changing radio-frequency power supply (101), that is, change the duty ratio of anti-deicing device, to subtract
The presence of few aerofoil surface overflow water, reduces the generation of ice tumor；Wherein, the optional adjustable range of pulse width is 1-500 μ s, arteries and veins
The optional adjustable range for rushing the period is 1-50ms.
11. the method that the anti-deicing of wing is carried out using rf (discharge) plasma excitation as claimed in claim 10, wherein
In step (a), apply radio-frequency voltage 2000V at the electrode both ends of anti-deicing device (103)；The liter of impedance matching circuit (102)
Pressure ratio is 1: 4, and resonant frequency is about 1.20MHz.
12. the method that the anti-deicing of wing is carried out using rf (discharge) plasma excitation as claimed in claim 10, wherein
In step (c), the output power for changing radio-frequency power supply (101) is 300W.
13. the method that the anti-deicing of wing is carried out using rf (discharge) plasma excitation as claimed in claim 10, wherein
In step (d), the working frequency for changing radio-frequency power supply (101) is 1.20MHz.
14. the method that the anti-deicing of wing is carried out using rf (discharge) plasma excitation as claimed in claim 10, wherein
In step (e), the pulse width of radio-frequency power supply (101) and pulse period are changed into 500 μ s and 5ms respectively.
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| CN109552644A (en) * | 2018-11-24 | 2019-04-02 | 中国人民解放军空军工程大学 | A kind of netted plasma heat knife |
| 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 |
| 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 |
| CN109941442A (en) * | 2019-03-11 | 2019-06-28 | 滨州学院 | A kind of electric pulse heat-mechanical aircraft deicing method and system combined |
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| CN115892477A (en) * | 2023-01-09 | 2023-04-04 | 中国空气动力研究与发展中心低速空气动力研究所 | Method and device for detecting plasma in icing range, storage medium, and program |
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| 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 |
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| 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 |
| CN113286391A (en) * | 2021-05-31 | 2021-08-20 | 华中科技大学 | Ice detecting and removing device and method |
| CN114104299A (en) * | 2021-11-26 | 2022-03-01 | 中国人民解放军空军工程大学 | Super-hydrophobic coating plasma and graphene electric heating composite ice preventing and removing device and method |
| CN114104299B (en) * | 2021-11-26 | 2024-03-12 | 中国人民解放军空军工程大学 | Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating |
| CN114071853A (en) * | 2021-12-03 | 2022-02-18 | 中国人民解放军空军工程大学 | Wing plasma stall prevention/anti-icing/deicing bimodal switching system and working method |
| CN114771804A (en) * | 2022-06-17 | 2022-07-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Asymmetric groove liquid film directional splashing pneumatic structure |
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| CN115892477A (en) * | 2023-01-09 | 2023-04-04 | 中国空气动力研究与发展中心低速空气动力研究所 | Method and device for detecting plasma in icing range, storage medium, and program |
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| CN116280213A (en) * | 2023-05-18 | 2023-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing thermal coupling deicing device and method |
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Application publication date: 20180918 |