CN108482683A - A kind of system and method using the anti-deicing of sliding discharge plasma - Google Patents
A kind of system and method using the anti-deicing of sliding discharge plasma Download PDFInfo
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- CN108482683A CN108482683A CN201810230378.9A CN201810230378A CN108482683A CN 108482683 A CN108482683 A CN 108482683A CN 201810230378 A CN201810230378 A CN 201810230378A CN 108482683 A CN108482683 A CN 108482683A
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- deicing
- discharge plasma
- sliding discharge
- icing
- top electrode
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- 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
Abstract
A kind of system using the anti-deicing of sliding discharge plasma of disclosure of the invention, including sliding discharge Plasma Actuator, icing detector, power-supply system and anti-deicing controller, power-supply system provide working power for each electrical equipment；Sliding discharge Plasma Actuator and icing detector are connect with anti-deicing controller respectively；Being specifically divided into using the method for the anti-deicing of sliding discharge plasma prevents from freezing and abolish two working stages of accumulated ice, large-scale sliding discharge is generated by using sliding discharge Plasma Actuator, generating fast energy injection makes sliding discharge Plasma Actuator upper surface whole region be rapidly heated, melt aerofoil surface and the accumulated ice at the interface of ice sheet bottom, aerofoil surface and ice sheet are detached from, solve the problems, such as that traditional hot gas anti-icing system fuel consumption is big on aircraft, heat utilization rate is low.
Description
Technical field
The invention belongs to plasma physics and anti-deicing technical field, and in particular to a kind of application sliding discharge plasma
The system of the anti-deicing of body, the invention further relates to the methods of the application anti-deicing of sliding discharge plasma.
Background technology
After aircraft encounters the super-cooling waterdrop in cloud layer in the air, the leading edge of a wing, empennage, rotor, engine inlets and
The positions such as windscreen may freeze.The flow field near aerofoil profile can be significantly affected when icing shape or irregular distribution, broken
The streamline shape of bad wing, makes that lift reduces, resistance increases, driving efficiency reduces, it is difficult to manipulate or even fails, motor power
The technical indicators such as reduction deteriorate, and directly result in and instantaneously slow down, fall, stall, lateral rolling, fiercely bowing, damage the gas of aircraft
Dynamic performance and operating characteristics, reduce the safety of flight.
In addition to super-cooling waterdrop and body surface temperature influence, when flying speed is in subsonic speed, atmospheric temperature is at 0 DEG C
To -20 DEG C, when 3000~7000 meters, aircraft is easier to freeze flying height, thus for big aircraft, large-scale military fortune
The type with high thrust, big Gross Weight Takeoff, subsonic speed, strong viability such as defeated machine, it is always the protrusion for influencing its safety to freeze
Hidden danger.Some dopeies, such as transporter, helicopter and unmanned plane, the possibility to freeze are also very big.It increases rain artificially work
When industry, due to increasing the needs on rain opportunity, aircraft is more easy to freeze.Therefore, when aircraft carries out Flight Test, it is necessary to freeze
Region is flown, and certification is carried out.
Ice formation issues will have a direct impact on the aeroperformance of aircraft, threaten the flight safety of aircraft, and machine may be caused when serious
Ruin the consequence that people dies.On March 5th, 1993, one frame good fortune gram of airline of Macedonia, 100 aircraft are climbed after taking off to 1200 feet
When there is stall, pilot can not manipulate aircraft, and aircraft is tilted to the left and rapid born, totally 97 people on machine, dead 81 people.Later stage
Investigation shows：Accident is caused by wing icing.On November 28th, 2004, a frame Pang Badi CL-601-2A12 are in section of U.S. sieve
Ground is hit after drawing more state Montrose field takeoffs, aircraft is on fire immediately.The Advisory Circulars identification of subsequent NTSB：When taking off,
Upper surface of the airfoil icing causes stall.On June 3rd, 2006, the sky alert -200 that a frame is under the jurisdiction of PLA Air Force are pre-
Alert machine has an accident in Guangde County of Anhui Province towns Bai Dian Mountain of Pear village overhead and crashes in the task of execution, on machine including crew
40 people be all murdered, this is the airplane crash of Chinese People's Liberation Army's most serious in history for army building, caused by loss be can not
It is weighed with money, that brave and noble-minded is all the elite of Chinese military secret research and development.The direct original of this incident is caused by verification
Because being due to once repeatedly passing through ice field, Aircraft Air freezes and crash out of control
According to the data statistics of the U.S. " aircraft owner and pilots association " (AOPA) aviation safety foundation, from 1975
Between year to 1988,30 and the relevant aircraft accident that freezes about occur every year on average, some times are even more than 50,
Wherein 50% accident includes personnel death.Between 10 years of 1990-2000, due to weather caused by aircraft accident it is total
3230, related totally 388 with icing, 12% is accounted for, wherein catastrophic failure 105 rises, and accounts for the 27% of accumulated ice accident.It unites in the U.S.
Meter data is shown：Economic loss is every year on average up to 0.96 hundred million dollars caused by aircraft freezes.Modern operation unmanned plane, especially
Scounting aeroplane, it is desirable that have can under IFR conditions the round-the-clock task that carries out ability, and icing meteorology condition is it
One of the threat for having to solve faced.It can be seen that aircraft icing problem is always by various countries' aviation and military service
Pay much attention to, in the aviation safety Technical Development Program that NASA (NASA) proposes, just using aircraft icing as excellent
One of three kinds of meteorological conditions first considered.
U.S. army goes on along in the anti-deicing field of aircraft in world forward position, and for China of west block in anti-deicing field
Development starting very late.This is because domestic lack the biography for largely using air power in bad weather and landform for a long time
System, therefore be abnormal think little of to the anti-deicing of aircraft.This results in the country, and largely the outmoded aircraft of basic engineering (include
Have man-machine, helicopter, unmanned plane etc.) poor ability of model reply harsh weather, round-the-clock full landform fight capability is seriously not
Foot is deficient to the research of the effective means of anti-deicing.
The difference prevented and kill off freezing cold section of foundation and use form of energy generally used at present, is mainly divided into：System of mechanical deicing
System, the anti-deicing system of chemical liquid and the anti-deicing system of heating power etc..
Pneumatic Boot Deicing System starts from last century three, the forties, mainly has two kinds of pneumatic cover deicing and Electro-Impulse De-icing, is
A kind of mechanical force is generated on the aircraft icing surface that need to be protected in the way of electricity, gas, sound wave etc., the knot of accumulated ice is destroyed using this power
Structure makes ice directly fall off from attaching surface or removes remaining accumulated ice using the effect of aerodynamic force.Pneumatically cover deicing system is swollen
Tube expansion can be affected to aircraft aerodynamic performance when inflating, and pneumatically cover can increase aging at any time, and need periodic maintenance,
Replace parts.This method can be used to remove surface accumulated ice without that can prevent the growth that freezes, therefore be not available as anti-icing equipment, at present
It has been rarely employed.Electroporation rises in last century the late sixties, due to system have light-weight, power consumption is low, energy conservation and environmental protection,
The features such as safety and stability, deicing work well, wing and the engine charge road junction of many modern aircrafts still use the technology,
But many regions such as the windshield of aircraft, sensor, radome, lifting airscrew and propeller blade are not suitable for making
It is obtained with electromagnetic interference problem with the fatigue properties of this method, and its current covering and is solved very well not yet, simultaneously because research
The considerations of multiple factors such as limitation and safety demonstration, electro-impulse deicing system, which is developed so far, to be still subject to certain restrictions.
The principle of the anti-deicing of chemical liquid is that the very low liquid of freezing point is sprayed at icing position, it is made to be mixed with subcooled water
Freezing point prevents to freeze less than the apparent freezing point of aircraft surfaces temperature or super-cooling waterdrop afterwards.Can be used as anti-freeze fluid has ethylene second two
Alcohol, isopropanol, ethyl alcohol etc..When technology anti-icing using liquid, the advantage is that will not form ice after the anti-icing surface of component
Tumor, and after stopping feed flow, the also anti-ice action with the short time.The technology is chiefly used in windscreen, radome, empennage leading edge appearance
The positions such as face.But because anti-icing fluid durability is poor, certain corrosion is will produce to substrate surface, and consumption is also generally large,
System weight can be made to increase, maintenance is more troublesome, if used anti-icing fluid is not environmentally protective, is also likely made to atmospheric environment
At pollution therefore relatively fewer use.
The most widely used on aircraft at present is the anti-deicing systems technology of heating power, which has become modern aircraft and prevent and kill off
The mainstream of ice technology development.But its energy consumption is very big, additional energy expenditure can be caused to bear to aircraft, and if heat provides
Deficiency, ice-out may be back to rear key position regelation later.
Thirst for always obtaining in the world it is a kind of " it is efficient, low energy consumption, light-weight, simple in structure, easy to maintain, reliability
It is high, aerodynamic configuration is influenced it is small " anti-deicing system, therefore, the anti-deicing of plasma has obtained continuous attention.Plasma stream
It is dynamic control be using plasma excitation improve aerodynamic characteristic new concept active Flow Control technology, have the response time it is short,
The technical advantages such as movement-less part, excitation frequency band be wide are controlled in wing lift-rising drag reduction, compressor stability-enhancement synergistic and Shock Wave Characteristics
Etc. make important progress, which was classified as ten aviation cutting edge technologies the (the 5th in 2009 by American Institute of Aeronautics and Astronautics
), it is of great significance for promoting military spacecraft aeroperformance.Plasma Actuator have the response time it is short, without fortune
The technical advantages such as dynamic component, excitation frequency band be wide, it is airborne to reducing as a kind of alternative potential means of the anti-deicing of aircraft
System is also significant.
Typical medium barrier plasma driver is by dielectric and its high-low pressure electrode of both sides asymmetric arrangement
Composition.Its work basic principle is：When the time ruler for the high voltage pulse rising edge or failing edge for being applied to actuator electrode both ends
For degree in magnitude of several nanoseconds to tens nanoseconds, electric discharge forms rapid energy deposition in plasmasphere, causes at nearly driver
Air be rapidly heated, the time less than 1 μ s, causes local gas rapid warm raising and pressure to rise, can stream field form flash and disturb
Dynamic even blast disturbance, i.e. plasma attack air-operated drive.What 8-12 days in January, 2018 held in Florida of the U.S.
In 2018AIAA air science conferences《A Comparison Study on AC-DBD Plasma and Electrical
Heating for Aircraft Icing Mitigation》One text proves：Dielectric barrier discharge plasma is encouraged in power consumption
It is more preferable than the anti-deicing effect of Electric radiant Heating Film under the conditions of lower.But abundant experimental results show：Medium barrier plasma
The aerodynamic force of driver induction is weaker, and the effective coverage for generating corona discharge is relatively narrow, is only limitted to upper/lower electrode intersection very little
Part, the heat being converted into is relatively low, is extremely difficult to the requirement of the anti-deicing of existing aircraft.
Invention content
The purpose of the present invention is to provide a kind of system using the anti-deicing of sliding discharge plasma, which plays
Low energy consumption, electric energy is to the advantage of thermal energy conversion efficiency height, fast response time, improves the performance of aircraft, expands aircraft safety
Flight envelope.
It is a further object to provide a kind of methods using the anti-deicing of sliding discharge plasma, solve winged
The problem that traditional hot gas anti-icing system fuel consumption is big on machine, heat utilization rate is low.
The technical solution adopted in the present invention is a kind of system using the anti-deicing of sliding discharge plasma, including cunning
Dynamic discharge plasma driver, icing detector, power-supply system and anti-deicing controller, power-supply system respectively with sliding discharge
Plasma Actuator, icing detector and the connection of anti-deicing controller；Sliding discharge Plasma Actuator and icing detection
Device is connect with anti-deicing controller respectively.
The features of the present invention also characterized in that
The structure of sliding discharge Plasma Actuator is：Including insulating medium layer, insulating medium layer bottom surface is equipped with down
Electrode layer, insulating medium layer upper surface are equipped with the first top electrode, the second top electrode and third top electrode, the first top electrode and third
Top electrode is located at the both sides of the second top electrode, and the second top electrode applies positive pulse high voltage VNP, the first top electrode and
Apply DC high voltage V in third top electrode respectivelyDC1With DC high voltage VDC2, it is entire to power on best third top electrode first
Uniformly sliding plasma discharge is formed in region.
First top electrode and third top electrode power on extremely axis mirror image distribution with second.
First top electrode, the second top electrode and third power on extremely three strip shaped electric poles being mutually parallel.
Another technical solution of the present invention is, a method of using the anti-deicing of sliding discharge plasma,
Anti- deicing is carried out to the easy ice field of aircraft using a kind of system of above-mentioned anti-deicing of sliding discharge plasma, the anti-deicing
Method be divided into and prevent from freezing and abolish two working stages of accumulated ice, specific implementation method is as follows：
It prevents from freezing：Sliding discharge Plasma Actuator is installed on aerofoil surface, icing detector is installed on winged
On the outside of machine head, when icing detector detects icing phenomenon, opens sliding discharge Plasma Actuator and carry out preventing from tying
Ice, the preheating generated to aerofoil surface by sliding discharge Plasma Actuator and pneumatic percussion, reaching wing prevents
The effect of icing；
Abolish accumulated ice：It is normaled cruise under state of flight when flight is in, icing detector is mounted on aircraft wing, empennage
At leading edge and engine inlets, when icing detector detects that aircraft local surfaces have weak icing phenomenon to occur, in conjunction with winged
When machine own control systems detect that lift coefficient has the amplitude reduction of 10%-30%, aircraft own control systems are alarmed at this time,
And anti-deicing controller is opened, and the icing degree and accumulated ice region that anti-deicing controller is detected according to icing detector, control
Region of discharge, discharge power and the running parameter of sliding discharge Plasma Actuator, sliding discharge Plasma Actuator pair
Ice field generates sliding plasma discharge, and generating fast energy injection keeps sliding discharge Plasma Actuator upper surface whole
A region is rapidly heated, and melts aerofoil surface and the accumulated ice at the interface of ice sheet bottom, and aerofoil surface is made to be detached from ice sheet.
The features of the present invention also characterized in that
Foundation when judging that aircraft local surfaces have weak icing phenomenon to occur by icing detector is：Icing intensity is less than
0.6 milli m/min, icing maximum gauge are 0.1-5.0 millimeters.
Sliding discharge Plasma Actuator to ice field generate sliding plasma discharge pulse frequency be：1-
1000 hertz, voltage value is：5000-10000 is lied prostrate.
The beneficial effects of the invention are as follows：
(1) the sliding discharge Plasma Actuator applied in the method for the present invention has the active regions ﹑ mono- Zhi Liang Qing ﹑ Jie structures Jian
The advantages that domain is big applies the polarity and intensity of high voltage by changing, can control driver spatial induction shock wave on electrode
Intensity and heat distribution, convenient for according to the temperature of aerofoil surface, the energy needed for closed-loop control driver reaches anti-deicing
Target.
(2) de-icing method of the invention, avoids that traditional hot gas anti-icing system fuel consumption is big, heat utilization rate is low lacks
Point, having played sliding discharge Plasma Actuator, low energy consumption, the advantage of electric energy to thermal energy conversion efficiency height, fast response time,
The performance for improving aircraft expands aircraft safety flight envelope.
(3) sliding discharge Plasma Actuator not only has the effect of flowing control lift-rising drag reduction, but also has both anti-deicing
Effect is expected to realize " set of device, two kinds of efficiency ".In addition its own is with reliability height, movement-less part, excitation frequency band
The technical advantages such as wide, small on aerodynamic configuration influence, as a kind of alternative potential means of the anti-deicing of aircraft, to reducing machine
Loading system is also significant.
Description of the drawings
Fig. 1 is the structural schematic diagram of sliding discharge Plasma Actuator in the present invention；
Fig. 2 is sliding discharge Plasma Actuator top electrode distribution map in the present invention；
Fig. 3 is distribution of electrodes figure under sliding discharge Plasma Actuator in the present invention；
Fig. 4 is that the system in the present invention using the anti-deicing of sliding discharge plasma constitutes schematic diagram；
Fig. 5 is the cloth of sliding discharge Plasma Actuator and icing detector on experimental model in the embodiment of the present invention
Office's figure.
In figure, 1. sliding discharge Plasma Actuators, 2. icing detectors, 3. power-supply systems, 4. anti-deicing controllers,
5. experimental model；The first top electrodes of 1-1., the second top electrodes of 1-2., 1-3. third top electrodes, 1-4. insulating medium layers, under 1-5.
Electrode layer.
Specific implementation mode
The following describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
The present invention provides a kind of system using the anti-deicing of sliding discharge plasma, as shown in figure 4, including sliding discharge
Plasma Actuator 1, icing detector 2, power-supply system 3 and anti-deicing controller 4, power-supply system 3 respectively with sliding discharge
Plasma Actuator 1, icing detector 2 and the connection of anti-deicing controller 4, power-supply system 3 provide work for each electrical equipment
Power supply；Sliding discharge Plasma Actuator 1 and icing detector 2 are connect with anti-deicing controller 4 respectively.
As shown in Figs. 1-3, the structure of sliding discharge Plasma Actuator 1 is：Including insulating medium layer 1-4, insulation is situated between
Matter layer 1-4 bottom surfaces are equipped with lower electrode layer 1-5, and the upper surfaces insulating medium layer 1-4 are equipped with the first top electrode 1-1, the second top electrode
1-2 and third top electrode 1-3, the first top electrode 1-1 and third top electrode 1-3 are located at the both sides of the second top electrode 1-2, the
Two top electrode 1-2 apply positive pulse high voltage VNP, apply direct current respectively on the first top electrode 1-1 and third top electrode 1-3
High voltage VDC1With DC high voltage VDC2, uniformly sliding is formed in the first top electrode 1-1 to third top electrode 1-3 whole regions
Plasma discharge.
First top electrode 1-1 and third top electrode 1-3 is distributed by axis mirror image of the second top electrode 1-2.
First top electrode 1-1, the second top electrode 1-2 and third top electrode 1-3 are three strip shaped electric poles being mutually parallel.
Positive pulse high voltage VNPIt is more than the high voltage of threshold voltage 5000V for peak-to-peak voltage value, when voltage peak-to-peak value
When higher than certain voltage range, the air-operated drive effect variation of sliding discharge Plasma Actuator 1 is little, and is easy breakdown
Driver, therefore Voltage Peak peak ranges are VNP=5000-20000V, preferably 10000V；Pulses range is Fp=1-
5000Hz, frequency is higher, and air-operated drive function and effect are more apparent, and when frequency is higher than a certain range, function and effect variation is little,
Therefore preferably Fp=100Hz；Millisecond, microsecond, nanosecond and radio-frequency pulse power supply, preferably nanosecond power supply can be selected in power type.
DC high voltage VDC1And VDC2Can be positive and negative direct current voltage, voltage value is excessive to be easy to swash in sliding discharge plasma
It encourages 1 surface of device and generates electric arc, therefore DC high voltage ranging from VDC=-15kV extremely+15kV, preferably VDC=-10kV.On first
The material of electrode 1, the second top electrode 2 and third top electrode 3 is metallic copper, but the material of electrode is not limited to copper, can meet and lead
Electrical property is good, secondary electron yield is high, heat conductivity is good, the other materials of the conditions such as at low cost also may be used.Dielectric
The high voltage bearing isolation materials such as the optional polytetrafluoroethylene (PTFE) of layer, polyimides, can select the higher insulating materials of dielectric constant,
Higher electric heating conversion energy can be generated.
The present invention provides a kind of method using the anti-deicing of sliding discharge plasma, is slided using a kind of above-mentioned application
The system of the anti-deicing of discharge plasma carries out anti-deicing to the easy ice field of aircraft, and the method for the anti-deicing, which is divided into, to be prevented from freezing
With abolish two working stages of accumulated ice, specific implementation method is as follows：
It prevents from freezing：Sliding discharge Plasma Actuator 1 is installed on aerofoil surface, connects anti-deicing controller 4, and
Power on system 3, icing detector 2 is installed on the outside of plane nose, when icing phenomenon occurs in the detection of icing detector 2
When, pilot can open plasma apparatus and carry out preventing from freezing, the wing generated by sliding discharge Plasma Actuator 1
Surface preheats and pneumatic percussion, achievees the effect that wing prevents from freezing；
Abolish accumulated ice：It is normaled cruise under state of flight when flight is in, icing detector 2 is mounted on aircraft wing, tail
At nose of wing and engine inlets, (freeze when icing detector 2 detects that aircraft local surfaces have weak icing phenomenon to occur
Intensity is less than 0.6 milli m/min, 0.1-5.0 millimeters of icing maximum gauge), detect lift system in conjunction with aircraft own control systems
When number has the amplitude reduction of 10%-30%, aircraft own control systems are alarmed at this time, and pilot is reminded to take correct flight
Operation, and anti-deicing controller 4 is opened, after the icing degree detected according to icing detector 2 and accumulated ice region, control sliding
Region of discharge, discharge power and the running parameter of discharge plasma driver 1, sliding discharge Plasma Actuator 1 is to knot
The sliding plasma discharge that ice formation domain generates 1-1000 hertz of pulse frequency, voltage value 5000-10000 is lied prostrate, generates quick energy
Amount injection makes 1 upper surface whole region of sliding discharge Plasma Actuator be rapidly heated, and melts aerofoil surface and ice sheet bottom
Accumulated ice at portion's interface makes aerofoil surface be detached from ice sheet.
By the adherency physical characteristic to ice research shows that：Shear adhesion intensity between ice and body surface (is usually not more than
Cross 1MPa or so) to be less than stretching adhesion strength (typically not greater than 2MPa or so, in special circumstances up to tens megapascal), therefore
It is easier to destroy the cohesive force between ice and surface using shear stress.It is inputted by controlling sliding discharge Plasma Actuator 1
Electrical parameter can generate asymmetric shock wave on driver surface, convert electrical energy into the kinetic energy of Motion Particles in air, be formed
Tangential impact aerodynamic force.Therefore, sliding discharge Plasma Actuator 1 is so that ice sheet is detached from electrical heating aerofoil surface
Make the resultant effect that ice sheet falls off with tangential impact aerodynamic force, the final ablation for realizing body surface ice sheet with fall off.Finally, lead to
It crosses icing detector 2 and detects weak icing phenomenon (icing intensity is less than 0.6 milli m/min, 0.1-5.0 millimeters of icing maximum gauge)
Whether eliminate, has judged whether that needing to adjust Plasma Actuator electrical parameter still closes the anti-deicing system of plasma.
Embodiment
As shown in figure 5, experimental model 5 is NACA0015 aerofoil profiles, chord length 300mm, length 500mm.Sliding discharge etc. from
The electrode of daughter driver 1 uses copper material, copper electrode to be embedded in soft Thin film silicone rubbers sheet surface, power-on and power-off
Identical processing has extremely been done, Thin film silicone rubbers thin slice is covered in airfoil surface along the tangential of aerofoil profile, forms sliding discharge etc.
Gas ions incentive structure.
Top electrode is made of three strip electrodes, the first top electrode 1-1 long 200mm, wide 5mm；Second top electrode 1-2 long 200mm,
Wide 5mm；Third top electrode 1-3 is mirror images of the first top electrode 1-1 centered on the second top electrode 1-2.
Insulating medium layer 1-4 is made of the Thin film silicone rubbers thin slice of thick 1mm.
Lower electrode layer 1-5 is long 200mm, and the monoblock copper electrode of wide 40mm forms.
The present embodiment selects carry-on wing as the application of anti-clearing ice technology.Icing detector 2 and sliding
Discharge plasma driver 1 is installed in the groove of the leading edge of a wing, and driver outer surface has that protective film is moisture-proof, and preventer
Part aging, but have no effect on the working condition of equal sliding discharges Plasma Actuator 1.Sliding discharge Plasma Actuator 1
Outer surface keeps flushing with wing cover surface, does not influence the air-driven type face of wing.
Sliding discharge Plasma Actuator 1, icing detector 2, power-supply system 3 and anti-deicing controller 4 collectively form
The anti-deicing system of sliding discharge plasma can complete icing condition detection, quickly anti-deicing, the anti-deicing system of feedback control
The functions such as parameter of uniting.The work step of whole system can be divided into according to icing degree to be prevented wing icing and abolishes wing accumulated ice two
A working stage.
It is to prevent wing icing first.The leading edge of a wing is that aircraft is easiest to, starts the position to freeze and air-flow change at first
Change violent region.It can not only play and prevent and kill off along chord length direction arrangement sliding discharge Plasma Actuator 1 from the leading edge of a wing
The effect of ice can also play the flowing control effect for increasing lift, reducing resistance, have in takeoff and landing and cruising condition
Conducive to the flight envelope of aircraft is expanded, increase safety redundancy.Carrying out wing with sliding discharge Plasma Actuator 1 prevents
It freezes, is that when detecting icing phenomenon by the icing detector 2 installed on the outside of plane nose, plasma is opened by pilot first
Body equipment carries out anti-freeze operation, the aerofoil surface preheating generated by sliding discharge Plasma Actuator 1 and Pneumatic immpacting
Effect achievees the effect that wing prevents from freezing.
It normals cruise under state of flight when flight is in, is installed on aircraft wing, empennage leading edge and engine inlets
(icing intensity is less than 0.6 milli m/min, freezes most when icing detector 2 detects that aircraft local surfaces have weak icing phenomenon to occur
Big 0.1-5.0 millimeters of thickness), when detecting that lift coefficient has the amplitude reduction of 10%-30% in conjunction with aircraft own control systems.
Aircraft control system is alarmed at this time, and pilot is reminded to take correct flight operation, and opens anti-deicing controller 4.It prevents and kill off
After icing degree that ice controller 4 is detected according to icing detector 2 and accumulated ice region, sliding discharge plasma excitation is controlled
Region of discharge, discharge power and the running parameter of device 1, driver generate 1-1000 hertz of pulse frequency, voltage to ice field
The sliding plasma discharge of value 5000-10000 volts.By sliding discharge Plasma Actuator 1 generate it is a wide range of grade from
Daughter is discharged, and generating fast energy injection makes 1 upper surface whole region of sliding discharge Plasma Actuator be rapidly heated, and melts
Change aerofoil surface and the accumulated ice at the interface of ice sheet bottom, aerofoil surface is made to be detached from ice sheet.It is special by the adherency physics to ice
Journal of Sex Research shows：Shear adhesion intensity (typically not greater than 1MPa or so) between ice and body surface, which will be less than, stretches adhesion strength
(typically not greater than 2MPa or so, in special circumstances up to tens megapascal), therefore destruction ice and surface are easier using shear stress
Between cohesive force.Electrical parameter is inputted by controlling sliding discharge Plasma Actuator 1, it is right to be generated on driver surface
The shock wave of title converts electrical energy into the kinetic energy of Motion Particles in air, forms tangential impact aerodynamic force.Therefore, sliding is put
Electro-plasma driver 1 makes ice sheet be detached from electrical heating aerofoil surface makes ice sheet fall off with tangential impact aerodynamic force
Resultant effect, the final ablation for realizing body surface ice sheet with fall off.Finally, weak freeze now is detected by icing detector 2
As if it is no eliminated, judge whether to need to adjust Plasma Actuator electrical parameter and still close the anti-deicing system of plasma
System.
Claims (7)
1. a kind of system using the anti-deicing of sliding discharge plasma, which is characterized in that swash including sliding discharge plasma
Encourage device (1), icing detector (2), power-supply system (3) and anti-deicing controller (4), power-supply system (3) respectively with sliding discharge
Plasma Actuator (1), icing detector (2) and anti-deicing controller (4) connection；Sliding discharge Plasma Actuator
(1) and icing detector (2) is connect with anti-deicing controller (4) respectively.
2. a kind of system using the anti-deicing of sliding discharge plasma according to claim 1, which is characterized in that described
The structure of sliding discharge Plasma Actuator (1) is：Including insulating medium layer (1-4), insulating medium layer (1-4) bottom
Face is equipped with lower electrode layer (1-5), and insulating medium layer (1-4) upper surface is equipped with the first top electrode (1-1), the second top electrode
(1-2) and third top electrode (1-3), first top electrode (1-1) and third top electrode (1-3) are located at the second top electrode
The both sides of (1-2), second top electrode (1-2) apply positive pulse high voltage VNP, first top electrode (1-1) and
Apply DC high voltage V respectively in three top electrodes (1-3)DC1With DC high voltage VDC2, in the first top electrode (1-1) to third
Uniformly sliding plasma discharge is formed in electrode (1-3) whole region.
3. a kind of system using the anti-deicing of sliding discharge plasma according to claim 2, which is characterized in that described
First top electrode (1-1) and third top electrode (1-3) are distributed with the second top electrode (1-2) for axis mirror image.
4. a kind of system using the anti-deicing of sliding discharge plasma according to claim 2, first top electrode
(1-1), the second top electrode (1-2) and third top electrode (1-3) are three strip shaped electric poles being mutually parallel.
5. a kind of method using the anti-deicing of sliding discharge plasma, which is characterized in that use as described in claim 1 one
Kind carries out anti-deicing using the system of the anti-deicing of sliding discharge plasma to the easy ice field of aircraft, the method point of the anti-deicing
To prevent from freezing and abolishing two working stages of accumulated ice, specific implementation method is as follows：
It prevents from freezing：Sliding discharge Plasma Actuator (1) is installed on aerofoil surface, icing detector (2) is installed on
On the outside of plane nose, when icing detector (2) detects icing phenomenon, open sliding discharge Plasma Actuator (1) into
Row prevents from freezing, and the preheating generated to aerofoil surface by sliding discharge Plasma Actuator (1) and pneumatic percussion reach
The effect for preventing from freezing to wing；
Abolish accumulated ice：It is normaled cruise under state of flight when flight is in, icing detector (2) is mounted on aircraft wing, empennage
At leading edge and engine inlets, when icing detector (2) detects that aircraft local surfaces have weak icing phenomenon to occur, in conjunction with
When aircraft own control systems detect that lift coefficient has the amplitude reduction of 10%-30%, aircraft own control systems report at this time
It is alert, and anti-deicing controller (4) is opened, the icing degree and product that anti-deicing controller (4) detects according to icing detector (2)
Ice formation domain, region of discharge, discharge power and the running parameter of control sliding discharge Plasma Actuator (1), sliding discharge etc.
Gas ions driver (1) to ice field generate sliding plasma discharge, generate fast energy injection make sliding discharge etc. from
Daughter driver (1) upper surface whole region is rapidly heated, and is melted aerofoil surface and the accumulated ice at the interface of ice sheet bottom, is made
Aerofoil surface is detached from ice sheet.
6. a kind of method using the anti-deicing of sliding discharge plasma according to claim 5, which is characterized in that pass through
Icing detector (2) judges that foundation when aircraft local surfaces have weak icing phenomenon to occur is：Icing intensity be less than 0.6 millimeter/
Point, icing maximum gauge is 0.1-5.0 millimeters.
7. a kind of method using the anti-deicing of sliding discharge plasma according to claim 5, which is characterized in that sliding
Discharge plasma driver (1) to ice field generate sliding plasma discharge pulse frequency be：1-1000 hertz, electricity
Pressure value is：5000-10000 is lied prostrate.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109334998A (en) * | 2018-11-24 | 2019-02-15 | 中国人民解放军空军工程大学 | A kind of gradient distribution formula plasma de-icing device and method |
| CN109573057A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Object plane accumulated ice sensor 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 |
| US10708979B2 (en) | 2016-10-07 | 2020-07-07 | De-Ice Technologies | Heating a bulk medium |
| CN112678188A (en) * | 2020-12-25 | 2021-04-20 | 武汉航空仪表有限责任公司 | Icing detector based on impedance measurement principle |
| CN113148183A (en) * | 2020-12-29 | 2021-07-23 | 重庆交通大学绿色航空技术研究院 | Plasma hot knife and hydrophobic material combined type deicing device and application |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101695959A (en) * | 2009-10-22 | 2010-04-21 | 北京航空航天大学 | Ice preventing and removing device for helicopter rotors |
| CN102798149A (en) * | 2012-07-26 | 2012-11-28 | 中国人民解放军装备学院 | Plasma concave-cavity flame stabilizer for engine |
| CN103410680A (en) * | 2013-06-19 | 2013-11-27 | 中国科学院电工研究所 | Plasma control device and method for blades of wind driven generator |
| CN104890881A (en) * | 2015-05-27 | 2015-09-09 | 西北工业大学 | Icing removing device and method of dielectric barrier discharge plasma |
| US20160003147A1 (en) * | 2013-02-06 | 2016-01-07 | Alenia Aermacchi S.P.A. | System for preventing icing on an aircraft surface operationally exposed to air |
| CN107072024A (en) * | 2017-02-09 | 2017-08-18 | 中国科学院电工研究所 | A kind of three electrode actuators device and methods of acquisition surface gliding spark discharge |
| CN107416181A (en) * | 2017-07-28 | 2017-12-01 | 中国人民解放军装备学院 | A kind of near space unmanned plane enhancing device |
-
2018
- 2018-03-20 CN CN201810230378.9A patent/CN108482683B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101695959A (en) * | 2009-10-22 | 2010-04-21 | 北京航空航天大学 | Ice preventing and removing device for helicopter rotors |
| CN102798149A (en) * | 2012-07-26 | 2012-11-28 | 中国人民解放军装备学院 | Plasma concave-cavity flame stabilizer for engine |
| US20160003147A1 (en) * | 2013-02-06 | 2016-01-07 | Alenia Aermacchi S.P.A. | System for preventing icing on an aircraft surface operationally exposed to air |
| CN103410680A (en) * | 2013-06-19 | 2013-11-27 | 中国科学院电工研究所 | Plasma control device and method for blades of wind driven generator |
| CN104890881A (en) * | 2015-05-27 | 2015-09-09 | 西北工业大学 | Icing removing device and method of dielectric barrier discharge plasma |
| CN107072024A (en) * | 2017-02-09 | 2017-08-18 | 中国科学院电工研究所 | A kind of three electrode actuators device and methods of acquisition surface gliding spark discharge |
| CN107416181A (en) * | 2017-07-28 | 2017-12-01 | 中国人民解放军装备学院 | A kind of near space unmanned plane enhancing device |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10708979B2 (en) | 2016-10-07 | 2020-07-07 | De-Ice Technologies | Heating a bulk medium |
| US11910493B2 (en) | 2016-10-07 | 2024-02-20 | De-Ice Technologies, Inc. | Heating a bulk medium |
| CN109334998A (en) * | 2018-11-24 | 2019-02-15 | 中国人民解放军空军工程大学 | A kind of gradient distribution formula plasma de-icing device and method |
| CN109573057A (en) * | 2018-11-24 | 2019-04-05 | 中国人民解放军空军工程大学 | Object plane accumulated ice sensor and its application method based on plasma |
| CN109573057B (en) * | 2018-11-24 | 2021-02-23 | 中国人民解放军空军工程大学 | Use method of object area ice sensor 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 |
| CN112678188A (en) * | 2020-12-25 | 2021-04-20 | 武汉航空仪表有限责任公司 | Icing detector based on impedance measurement principle |
| CN113148183A (en) * | 2020-12-29 | 2021-07-23 | 重庆交通大学绿色航空技术研究院 | Plasma hot knife and hydrophobic material combined type deicing device and application |
| 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 |
| CN115892477B (en) * | 2023-01-09 | 2023-05-02 | 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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