CN106314800A - Ice breaking and removing method based on plasma impact jet flow - Google Patents
Ice breaking and removing method based on plasma impact jet flow Download PDFInfo
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- CN106314800A CN106314800A CN201610841778.4A CN201610841778A CN106314800A CN 106314800 A CN106314800 A CN 106314800A CN 201610841778 A CN201610841778 A CN 201610841778A CN 106314800 A CN106314800 A CN 106314800A
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- plasma
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- icing
- plasma actuator
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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
The invention discloses an ice breaking and removing method based on plasma impact jet flow. In an easily-icing zone of an object with the ice removing demand, a plasma actuator and an icing detector are installed in the mode of being flush with the object plane of the easily-icing zone, wherein the plasma actuator and the icing detector are connected with a controller; when the icing detector detects that the object plane of the easily-icing zone ices, the controller controls the plasma actuator located in the easily-icing zone to work and controls the discharging power and frequency and the working time of the plasma actuator, and periodic high-temperature and high-dynamic-pressure jet flow generated by the plasma actuator is used for impacting an ice layer to make the ice layer rapidly vibrate, deform and break and even directly crushing and thawing the ice layer to achieve ice breaking. The plasma ice removing technology makes electric parameter control, light-and-small design and distributed layout easy, has the advantages of rapidness, high efficiency and low energy consumption and can be widely applied to ice breaking and removing for various air vehicles or other objects with the ice removing demand.
Description
Technical field
The invention belongs to deicing technology, plasma physics applied technical field, relate to a kind of based on plasma
The broken de-icing method of body impact jet flow, has the surface area of deicing demand object in order to quickly to abolish all kinds of aircraft or other
Ice.
Background technology
Icing phenomenon is prevalent in the middle of engineering practice and application, such as the transmission line of electricity under severe cold environment, at low temperature
In sleety weather, ambient humidity is high, and a large amount of Moisture condensation cause icing in conductive line surfaces, and during icing, the tension force of electric pole/tower both sides is not
Balance, it may appear that fall the fault such as bar/tower, causes power system to cut off.All kinds of aircraft are also had the most easily to meet with in flight course
Meeting and freeze, when aircraft flight under the conditions of subfreezing icing meteorology, the super-cooling waterdrop in air strikes aircraft surfaces,
It is easy to occur to freeze now at parts surfaces such as wing, empennage, rotor, air intake duct, windshield, antenna house, gauge sensor
As, not only increase the weight of aircraft, and destroy the aerodynamic configuration of aircraft surfaces, change Flow Field, destroy gas
Dynamic performance, easily causes flight safety accident.
The main deicing technology of current practice has heating power deicing method, mechanical deicing's method, passive deicing method etc.
Method.Passenger plane generally uses the method for machinery, gas heat or electric heating to carry out deicing, and both common ground are all to destroy between ice sheet and eyelid covering
Adhesion strength.But traditional mechanical de-icing method can change aerodynamic configuration, and eyelid covering vibration can cause structural fatigue.
Tradition steam jet needs pipeline supply system, and heat utilization ratio is relatively low and bleed air line can increase aircraft weight,
The anti-deicing of electric heating is of limited application and power consumption is big.
It addition, in the exploration of clearing ice technology, it is thus proposed that use dielectric barrier discharge plasma activator to remove
Ice, the main deicing principle of the method is the Joule heating effect of gas discharge, and the dielectric barrier discharge plasma of use swashs
Encourage device insulating cement to be pasted onto aircraft skin surface and easily freeze position, and positive and negative electrode has half to be exposed to, in the middle of air, deposit
Directly easily lost efficacy with air contact at change of flight device aerodynamic configuration, electrode, Plasma Actuator caloric value limited
Problem, and when flight under aircraft is at bad weather condition, icing intensity is big, and icing rate is fast, and pneumatic harm is big, and medium hinders
It is the most inadequate that gear discharge plasma activator carries out deicing deicing speed.
Thus need a kind of broken de-icing method more rapidly and efficiently badly, it is to avoid freeze the aircraft stall out of control caused.
Summary of the invention
In order to overcome deficiency of the prior art, the present invention provides a kind of and based on plasma attack jet abolishes ice side
Method.The plasma clearing ice technology that the present invention proposes is prone to electrical quantity control, small light and distributed arrangement, have quickly,
Efficiently, the feature of low energy consumption.
For realizing above-mentioned technical purpose, the technical scheme is that,
A kind of broken de-icing method based on plasma attack jet, installs in the easy ice field having deicing demand object
The Plasma Actuator of high temperature high dynamic pressure jet can be sprayed, when occurring in easy ice field to freeze, utilize plasma to swash
Encourage the periodic high temperature high dynamic pressure jet impulse ice sheet fast vibration deformation fracture that device produces, the most directly smash and melt ice
Layer, opens ice.
Further, in the easy ice field having deicing demand object, flushly mount with this easy ice field object plane
Gas ions activator and icing detector, Plasma Actuator and icing detector are all connected with a controller, visit when freezing
When survey device detects this easy ice field object plane generation icing, controller controls to be positioned at the plasma at this easy ice field and swashs
Encourage device work, and control the discharge power of Plasma Actuator, frequency and working time, utilize the periodic high temperature that it produces
High dynamic pressure jet impulse ice sheet fast vibration deformation fracture, the most directly smashes and melts ice sheet, opening ice.
Described Plasma Actuator relies on spark discharge to produce plasma heating gas synthesis jet.It can obtain
High speed impact jet.Plasma Actuator can be two electrode plasma activators, it would however also be possible to employ three electrode ion bodies
Activator.Two electrode discharges in two electrode plasma activators produce plasma, plasma heating intracavity gas, make
The temperature and pressure of intracavity gas quickly raises, and the intracavity gas of the pressurization that heats up, from outlet ejection at a high speed, forms speed and reaches hundreds of
The plasma jet of metre per second (m/s), causes under cavity negative pressure and cavity temperature and pressure due to the injection of high-speed jet afterwards
Fall, extraneous gas can refill cavity, completes pulsatile once jet, and going round and beginning again can form high-frequency high-speed high temperature pulse and penetrate
Stream.
Three electrode ion body activators are a kind of novel Plasma Actuators, add ignitor, and it is by one
Have the outlet dielectric chamber of slit, a pair main discharge electrode and an ignitor composition.During its work, it first it is ignition power
Pole electric discharge between electrode formed plasma conducts electricity passage, trigger main electrode electric discharge produce plasma, thereafter work process with
Two electrode actuators are identical.Experiment shows, the three electrode plasma activator nearly 1000K of heating cavity gas temperature, synthesis is penetrated
Flow Velocity is more than 500m/s, and compared with two electrode actuators, under atmospheric pressure, air puncture voltage is dropped to by 3kV/mm
0.8kV/mm, energy conversion efficiency improves about 4 times, and under identical discharge voltage condition, jet momentum improves 1 magnitude, and jet moves
Nearly 2 magnitudes can be improved.
Above-mentioned broken de-icing method based on plasma attack jet can be applicable on aircraft.There is deicing on board the aircraft
On the easy ice field such as wing of demand object, it is mounted flush against Plasma Actuator and icing detector with this region surface.
A kind of broken deicing system based on plasma attack jet, including Plasma Actuator, icing detector, electricity
Origin system and controller, power-supply system provides working power for each electrical equipment.In the easy ice field having deicing demand object
In, flushly mount with Plasma Actuator and icing detector, Plasma Actuator and icing with this easy ice field object plane
Detector is all connected with a controller, and described icing detector is used for detecting whether this easy ice field object plane freezes,
And the signal detected is sent to controller；The signal that controller detects according to icing detector controls plasma excitation
The duty of device, when icing detector detects this easy ice field object plane generation icing, it is easy that controller controls to be positioned at this
Plasma Actuator work at ice field, and control the discharge power of Plasma Actuator, frequency and working time,
Utilize the periodic high temperature high dynamic pressure jet impulse ice sheet fast vibration deformation fracture that it produces, the most directly smash and melt ice
Layer, opens ice, and freezes after removing, and signal is fed back to controller by icing detector, controls Plasma Actuator and terminates work
Make.
Further, described Plasma Actuator uses three electrode ion body activators.Three electrode ion body activators
Including activator positive pole, activator negative pole, ignitor, cavity and cavity cover plate, increasing ignitor can be greatly reduced
Air puncture voltage in activator work process, raising energy of the impinging jet.The outlet of Plasma Actuator is had on cavity cover plate,
Cavity cover plate is concordant with easy ice field object plane, does not affect the integral surface configuration of application.Ignitor electric discharge during work,
Between activator positive pole, activator negative pole, form plasma conducts electricity passage, trigger activator positive pole, activator negative pole two electrode
Electric discharge produces plasma, gas in plasma heating cavity, makes the temperature and pressure of gas in cavity quickly raise, heats up
Gas outlet from cavity cover plate ejection at a high speed in the cavity of pressurization, the plasma that formation speed reaches hundreds of meters per second is penetrated
Stream, causes the decline of cavity negative pressure and cavity inner temperature and pressure due to the injection of high-speed jet afterwards, and extraneous gas can weigh
New filling cavity, completes pulsatile once jet, goes round and begins again and can form high-frequency high-speed high temperature pulse jet.
Further, described in have deicing demand object be aircraft, its easy ice field includes wing.
The method of using plasma impact jet flow of the present invention abolishes the accumulated ice of aircraft or other subject surface, it is to avoid
Traditional mechanical de-icing method can change aerodynamic configuration or eyelid covering vibrates the structural fatigue problem caused, it is to avoid traditional steam is penetrated
Stream needs the problem of pipeline supply system, and the problem that the anti-deicing of electric heating is of limited application and power consumption is big.Specifically have with
Lower advantage:
1, it is prone to small light.
Three electrode plasma synthesizing jet-flow excitor own vols are little, light weight, energy efficiency high, mechanical Actuator Division
Part, without source of the gas and pipeline supply system, without extra heater, it is to avoid the structure design of anti-deicing system complex, the most easily
In small light；
2, electrical quantity control it is prone to.
Only need to consume electric energy during three electrode plasma synthesizing jet-flow excitor work, can facilitate by controlling ignitor
Realize startup and the FREQUENCY CONTROL of activator, and working band width, response are thus susceptible to rapidly electrical quantity control；
3, it is prone to distributed arrangement.
Three electrode plasma synthesizing jet-flow excitors without complicated source of the gas pipeline, only simple power circuit, and volume
Little, adaptive capacity to environment is strong, it is easy to carry out distributed arrangement's encapsulation, and will not the structure of change of flight device and aerodynamic configuration；
4, speed of icing is abolished fast.
Ice Breaking System based on plasma attack jet is by Plasma Actuator, icing detector and controller group
Becoming, use closed loop control, the plasma jet that activator produces is except there being the heat of dielectric barrier discharge plasma activator
Outside effect, also having high speed and high pressure shock effect, from freezing to producing, ice is abolished in impact jet flow, and the time is short, speed is fast.
5, energy consumption is low.
The high temperature high dynamic pressure pulsing jet that Plasma Actuator produces, only need to consume electric energy during work, the time of opening ice is short,
Pulse jet energy consumption is low, and overall energy consumption is the lowest.
Accompanying drawing explanation
Fig. 1 is that the present invention is based on plasma attack jet abolishes ice system schematic；
Fig. 2 is Plasma Actuator perspective view of the present invention；
Fig. 3 is that Plasma Actuator of the present invention is at fixed wing airplane wing distribution array schematic diagram.
In figure, each label represents:
1, Plasma Actuator；11, activator positive pole；12, activator negative pole；13, ignitor；14: cavity cover plate；
15: outlet；16: cavity；2, icing detector；3, power-supply system；4, controller；5, wing.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with accompanying drawing to embodiment party of the present invention
Formula is described in further detail.
The present embodiment chooses carry-on wing as the application opened ice, as it is shown in figure 1, plasma excitation
Device 1 and icing detector 2 are installed on wing 5.It is provided with on wing 5 for installing Plasma Actuator 1 and the spy that freezes
Survey the installing hole of device 2.Plasma Actuator 1 and icing detector 2 are arranged on wing 5 in corresponding installing hole, and etc.
Gas ions activator 1 and icing detector 2 install its outer surface rear and all flush with the aerofoil surface at its place wing,
The most both will not protrude also will not be recessed so that is mounted with wing pneumatic of broken deicing system based on plasma attack jet
Profile is unaffected, good integrity.
Plasma Actuator 1, icing detector 2, power-supply system 3, controller 4 together form complete based on etc. from
The broken deicing system of daughter impact jet flow, it is possible to realize icing detection, electric discharge decision-making, the function that quickly opens ice.Power-supply system is
Each electrical equipment provides working power.In the easy ice field having deicing demand object, concordant with this easy ice field object plane
Plasma Actuator is installed and icing detector, Plasma Actuator and icing detector are all connected with a controller, institute
State icing detector for detecting whether this easy ice field object plane freezes, and be sent to the signal detected control
Device；Controller controls the duty of Plasma Actuator according to the signal that icing detector detects.Work as icing detector
When detecting this easy ice field object plane generation icing, controller is according to the distribution frozen and the corresponding plasma of thickness selective exitation
Body activator 1 works continuously, and controls the discharge power of Plasma Actuator, frequency and working time, utilizes it to produce
Periodic high temperature high dynamic pressure jet, under the impact of wing internal plasma jet and outer gas stream, it is achieved aerofoil surface ice
Removal after, icing detector 2 signal feeds back to controller 4, controls Plasma Actuator 1 power cut-off.
The Plasma Actuator 1 that the present invention uses is three electrode plasma activators, as in figure 2 it is shown, it has three electricity
Pole, is activator positive pole 11, activator negative pole 12, ignitor 13, cavity 16 and cavity cover plate 14 respectively, increases ignition power
Pole 13 can be greatly reduced the air puncture voltage in activator work process, improve energy of the impinging jet.Have on cavity cover plate 14
The outlet 15 of gas ions activator 1, cavity cover plate 14 and wing 5 flush with outer surface, do not affect aerofoil surface configuration.Work time point
Fire electrode discharge, forms plasma conducts electricity passage between activator positive pole, activator negative pole, triggers activator positive pole, excitation
Device negative pole two electrode discharge produces plasma, gas in plasma heating cavity, makes the temperature and pressure of gas in cavity
Quickly rising, gas outlet from cavity cover plate ejection at a high speed in the cavity of pressurization that heats up, it is per second that formation speed reaches hundreds of meters
Plasma jet, cause the decline of cavity negative pressure and cavity inner temperature and pressure due to the injection of high-speed jet afterwards,
Extraneous gas can refill cavity, completes pulsatile once jet, goes round and begins again and can form high-frequency high-speed high temperature pulse jet.
Several Plasma Actuators 1 can be arranged in a particular embodiment in the easy ice field of wing；Plasma excitation
Device 1 concordant coil insertion device wing surface, does not bring any parasite drag, accompanying drawing 3 to give Plasma Actuator 1 on aircraft wing
An object lesson of overall distribution, be respectively uniformly distributed 10 plasma excitations at wing near the upper and lower surface of leading edge
Device 1, in actual applications, the number of Plasma Actuator 1, distribution and exit angle are by the needs according to concrete application
And optimal design-aside.
The present invention can substitute the methods such as traditional mechanical deicing, traditional steam jet, without traditional mechanical de-icing method band
The change aerodynamic configuration come or eyelid covering vibrate the structural fatigue problem caused, without tradition steam fluid conduit supply system,
At aspects such as small light, distributed arrangement, electrical quantity controls, there is advantage.Particularly body surface under bad weather condition
When icing intensity is very big, this method is capable of quickly abolishing ice.Present invention firstly provides and plasma attack jet is applied
In clearing ice technology field, can be widely applied to all kinds of aircraft or other have a deicing demand object abolish ice.
The explanation of the preferred embodiment of the present invention contained above, this is the technical characteristic in order to describe the present invention in detail, and
Be not intended to be limited in the concrete form described by embodiment summary of the invention, carry out according to present invention purport other
Amendment and modification are also protected by this patent.The purport of present invention is to be defined by the claims, rather than by embodiment
Specifically describe and defined.
Claims (10)
1. a broken de-icing method based on plasma attack jet, it is characterised in that: there iing the easy knot of deicing demand object
The Plasma Actuator that can spray high temperature high dynamic pressure jet is installed in territory, ice formation, when occurring in easy ice field to freeze, utilizes
The periodic high temperature high dynamic pressure jet impulse ice sheet fast vibration deformation fracture that Plasma Actuator produces, the most directly smashes
With thawing ice sheet, open ice.
Broken de-icing method based on plasma attack jet the most according to claim 1, it is characterised in that having deicing
In the easy ice field of demand object, flushly mount with Plasma Actuator and icing detector with this easy ice field object plane,
Plasma Actuator and icing detector are all connected with a controller, when icing detector detects this easy ice field object plane
When occurring to freeze, controller controls the Plasma Actuator work being positioned at this easy ice field, and it is sharp to control plasma
Encourage the discharge power of device, frequency and working time, utilize its periodic high temperature high dynamic pressure jet impulse ice sheet produced quickly to shake
Dynamic deformation ruptures, and the most directly smashes and melts ice sheet, opens ice.
Broken de-icing method based on plasma attack jet the most according to claim 1 and 2, it is characterised in that described
Plasma Actuator relies on spark discharge to produce plasma heating gas synthesis jet.
Broken de-icing method based on plasma attack jet the most according to claim 3, it is characterised in that plasma
Activator uses two electrode plasma excitations.
Broken de-icing method based on plasma attack jet the most according to claim 3, it is characterised in that described grade from
Daughter activator uses three electrode ion body activators.
6. according to a kind of based on plasma attack jet the broken de-icing method described in claim 1, it is characterised in that the party
Method is applied to carry-on easy ice field.
7. a broken deicing system based on plasma attack jet, it is characterised in that: include Plasma Actuator, icing
Detector, power-supply system and controller, power-supply system provides working power for each electrical equipment；
In the easy ice field having deicing demand object, with this easy ice field object plane flushly mount with Plasma Actuator and
Icing detector, Plasma Actuator and icing detector are all connected with a controller；
Described icing detector is used for detecting whether this easy ice field object plane freezes, and is sent by the signal detected
To controller；
Controller controls the duty of Plasma Actuator according to the signal that icing detector detects, and works as icing detector
When detecting this easy ice field object plane generation icing, controller controls to be positioned at the Plasma Actuator at this easy ice field
Work, and control the discharge power of Plasma Actuator, frequency and working time, utilize its periodic high temperature height produced to move
Jet flow impact ice sheet fast vibration deformation fracture, the most directly smashes and melts ice sheet, opening ice；Freeze after removing, knot
Signal is fed back to controller by ice sounder, controls Plasma Actuator power cut-off.
Broken deicing system based on plasma attack jet the most according to claim 7, it is characterised in that remove described in:
Ice demand object is aircraft, and its easy ice field includes wing, wing is provided with for install Plasma Actuator and
The installing hole of icing detector.Plasma Actuator and icing detector are arranged on wing in corresponding installing hole, and
Plasma Actuator and icing detector install its outer surface rear and all flush with the aerofoil surface at its place wing.
9. according to based on plasma attack jet the broken deicing system described in claim 7 or 8, it is characterised in that: described
Plasma Actuator uses three electrode ion body activators.
Broken deicing system based on plasma attack jet the most according to claim 9, it is characterised in that: three electrodes
Gas ions activator includes activator positive pole, activator negative pole, ignitor, cavity and cavity cover plate, and cavity cover plate has
The outlet of Plasma Actuator, cavity cover plate is concordant with easy ice field object plane after installing；
Ignitor electric discharge during work, forms plasma conducts electricity passage between activator positive pole, activator negative pole, triggers excitation
Device positive pole, activator negative pole two electrode discharge produce plasma, gas in plasma heating cavity, make gas in cavity
Temperature and pressure quickly raises, gas outlet from cavity cover plate ejection at a high speed in the cavity of pressurization that heats up, and forms speed and reaches
The plasma jet that hundreds of meters is per second, causes cavity negative pressure and cavity inner temperature and pressure due to the injection of high-speed jet afterwards
The decline of power, extraneous gas can refill cavity, completes pulsatile once jet, goes round and begins again and can form high-frequency high-speed high-temperature pulse
Rush jet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610841778.4A CN106314800A (en) | 2016-09-23 | 2016-09-23 | Ice breaking and removing method based on plasma impact jet flow |
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| CN201610841778.4A CN106314800A (en) | 2016-09-23 | 2016-09-23 | Ice breaking and removing method based on plasma impact jet flow |
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| CN201610841778.4A Pending CN106314800A (en) | 2016-09-23 | 2016-09-23 | Ice breaking and removing method based on plasma impact jet flow |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107444614A (en) * | 2017-09-08 | 2017-12-08 | 中国民航大学 | Suitable for the aerofoil flexibility plasma drag reduction paster of small-sized Fixed Wing AirVehicle |
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN108016622A (en) * | 2017-11-25 | 2018-05-11 | 中国商用飞机有限责任公司 | A kind of anti-icing method and device of active aircraft |
| CN108058832A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of combined type anti-freeze fluid-anti-deicing system of air bag |
| CN109250073A (en) * | 2018-09-30 | 2019-01-22 | 中国人民解放军国防科技大学 | Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet |
| CN109618481A (en) * | 2018-12-14 | 2019-04-12 | 哈尔滨工业大学 | The plasma synthesis jet-flow excitor of low reynolds number condition |
| 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 |
| CN111717400A (en) * | 2020-06-16 | 2020-09-29 | 中国人民解放军国防科技大学 | Adhesion force weakening and plasma high-energy exciter combined deicing device and method |
| 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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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444614A (en) * | 2017-09-08 | 2017-12-08 | 中国民航大学 | Suitable for the aerofoil flexibility plasma drag reduction paster of small-sized Fixed Wing AirVehicle |
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN108058832A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of combined type anti-freeze fluid-anti-deicing system of air bag |
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| CN109250073A (en) * | 2018-09-30 | 2019-01-22 | 中国人民解放军国防科技大学 | Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet |
| CN109618481A (en) * | 2018-12-14 | 2019-04-12 | 哈尔滨工业大学 | The plasma synthesis jet-flow excitor of low reynolds number condition |
| 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 |
| CN111717400A (en) * | 2020-06-16 | 2020-09-29 | 中国人民解放军国防科技大学 | Adhesion force weakening and plasma high-energy exciter combined deicing device and method |
| 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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