CN105704901A - Honeycomb-type dielectric barrier discharge plasma propelling device - Google Patents
Honeycomb-type dielectric barrier discharge plasma propelling device Download PDFInfo
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- CN105704901A CN105704901A CN201610111571.1A CN201610111571A CN105704901A CN 105704901 A CN105704901 A CN 105704901A CN 201610111571 A CN201610111571 A CN 201610111571A CN 105704901 A CN105704901 A CN 105704901A
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
- H05H1/2443—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes the plasma fluid flowing through a dielectric tube
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Abstract
The present invention provides a honeycomb-type dielectric barrier discharge plasma propelling device. The device comprises housing, a high-voltage power supply and a honeycomb structure arranged in the housing; and M layers of high-voltage electrodes are arranged on insulating dielectric walls in each honeycomb pore along the axial direction of the honeycomb structure, M layers of grounding electrodes are arranged at the positions where the insulating dielectric walls and the high-voltage electrodes are interleaved, and adjacent two layers of high-voltage electrodes and two layers of grounding electrodes form a dielectric barrier discharge plasma exciter. Because the main part of the device provided by the invention is a honeycomb structure, the honeycomb-type dielectric barrier discharge plasma propelling device is simple in structure, light in weight and low in manufacturing cost; the honeycomb-type dielectric barrier discharge plasma propelling device is fast in response and high in reliability because of having no motion parts; the honeycomb-type dielectric barrier discharge plasma propelling device is able to control the voltage and the frequency of a high-voltage power supply, flexibly set the excitation intensity and the power consumption, accurately control the size of thrust and regulate the axial direction of the honeycomb structure so as to regulate the direction of the thrust; and moreover, when being applied to an airship, the honeycomb-type dielectric barrier discharge plasma propelling device is able to realize accurate control of the motion speed and the motion direction of the airship and realize staying of the airship in the sky for a long time with no need for carrying fuel.
Description
Technical field
The present invention relates to propeller technical field, particularly relate to a kind of honeycomb type dielectric barrier discharge plasma propulsion plant, it is particularly well-suited to dirigible。
Background technology
Stratosphere refers generally to be positioned off the spatial domain of km～50, earth's surface 18 km, is one layer of upper heat and lower cold in earth atmosphere, is also the joint portion of the big system of earth observation Aeronautics and Astronautics two simultaneously。Stratosphere is the tranquilest in atmosphere one section, it is little affected by weather impact, also moist scarcely ever, simultaneously, stratosphere also has stable meteorological condition and good electromagnetic property, and limits currently without spatial domain, so, in view of motion feature and unique advantage of stratosphere self, it becomes the new focus of flourishing big powers' competition space resources。
Stratospheric airship is because of the feature that its uniqueness long-term stays fixed point empty, motor-driven, energy consumption is low, safety is high, and potential application prospect includes: the civil and military fields such as scientific research, communication relay and military surveillance。Owing to stratospheric airship needs long-term in sky, if adopting the traditional propulsion mode carrying fuel, two aspect problems can be brought: one is that the fuel carried can not long run supply；Two are, along with the consumption of fuel, the weight of dirigible produces change, and trim and the counterweight of dirigible are disadvantageous by this。Therefore, traditional engine propulsion system carrying fuel cannot be applied to stratospheric airship, and this area needs a kind of propulsion plant suitable in dirigible badly。
Summary of the invention
(1) to solve the technical problem that
In order to solve the problems referred to above that prior art exists, the invention provides a kind of honeycomb type dielectric barrier discharge plasma propulsion plant。
(2) technical scheme
The invention provides a kind of honeycomb type dielectric barrier discharge plasma propulsion plant, including: shell 101, high voltage power supply 107 and the honeycomb texture 102 being arranged in described shell, wherein, described honeycomb texture includes dielectric wall 103 and described dielectric wall 103 forms N number of honeycomb hole 104, it is provided with M shell high-field electrode 105 along the honeycomb texture axially described dielectric wall in each honeycomb hole, the position that described dielectric wall interlocks with described M shell high-field electrode is provided with M shell ground electrode 106, high-field electrode 105 and ground electrode 106 connect described high voltage power supply 107, wherein adjacent two layers high-field electrode 105 and ground electrode 106 form dielectric barrier discharge plasma activator, adjacent cell hole 104 shares the ground electrode 106 of its total dielectric wall, wherein, 1≤N≤1000, 1≤M≤1000。
Preferably, the position that described dielectric wall and described M shell high-field electrode interlock is provided with described M shell ground electrode 106 and specifically includes: position staggered with described M shell high-field electrode outside the dielectric wall of the outermost edges of described honeycomb texture is provided with described M shell ground electrode 106, and all the other dielectric pars intramuralis of described honeycomb texture position staggered with described M shell high-field electrode is inlaid with described M shell ground electrode 106, adjacent cell hole 104 shares the ground electrode 106 that its total dielectric pars intramuralis is inlayed。
Preferably, every layer of high-field electrode in described each honeycomb hole is connected as a single entity, form the annular high voltage electrode that M shell is identical with described honeycomb hole shape, the ground electrode that adjacent dielectric wall is arranged is connected as a single entity, forming M shell and have the Integral grounding electrode of N number of honeycomb hole, the annular high voltage electrode identical with described honeycomb hole shape with the M shell in described N number of honeycomb hole is corresponding。
Preferably, the dielectric wall arranged outside of the outermost edges of described honeycomb texture has insulant 109, and the ground electrode of the dielectric wall arranged outside of described outermost edges is covered by described insulant 109。
Preferably, also include: high-field electrode wire, ground electrode wire and lay respectively at N number of high-field electrode line post 110 at two ends and a ground electrode line post 111 of described honeycomb texture；Wherein, described M shell high-field electrode in described each honeycomb hole is linked together by described high-field electrode wire, and it is connected to described high-field electrode line post 110, it is then connected to high voltage power supply high-pressure side 112, M shell is had the Integral grounding electrode of N number of honeycomb hole and links together by described ground electrode wire, and it is connected to described ground electrode line post 111, it is then connected to high voltage power supply earth terminal 113。
Preferably, also including: solaode, it connects described high voltage power supply 107 and provides electric energy for described high voltage power supply 107。
Preferably, the cross section of described shell is hexagon, circle, tetragon or other polygons；And/or described honeycomb hole be shaped as hexagon, triangle, tetragon or other polygons。
Preferably, described dielectric wall and insulant are politef, quartz glass or ceramic material。
Preferably, the output waveform of described high voltage power supply is sinusoidal wave, square wave or sawtooth waveforms。
Preferably, the material of described high-field electrode and ground electrode is copper, tungsten, molybdenum or rustless steel。
(3) beneficial effect
From technique scheme it can be seen that the honeycomb type dielectric barrier discharge plasma propulsion plant of the present invention has the advantages that
(1) its critical piece is honeycomb texture, simple and compact for structure, low cost of manufacture；Not having moving component, response is rapid and reliability is high；
(2) honeycomb texture intensity is good, it is possible to adopt relatively thin materials processing, is conducive to alleviator weight, and adjacent cell hole shares the ground electrode of dielectric wall and the grounding electrode structure of integration, further mitigates weight, simplifies structure；
(3) high voltage power supply connects high-field electrode and ground electrode, by controlling voltage and the frequency of high voltage power supply, intensity and power consumption, the thrust size accurately controlling generation of plasma excitation can be set flexibly, when it is applied to dirigible, it is possible to achieve the accurate control of dirigible movement velocity；
(4) direction of the axis direction and adjustable thrust by adjusting honeycomb texture, when it is applied to dirigible, it is possible to achieve controlling flexibly and accurately of the dirigible direction of motion；
(5) electric energy consumed is provided by solaode, when for dirigible, it is not necessary to carry fuel, it is possible to achieve the long-term of dirigible stays sky；
(6) ground electrode is embedded in dielectric pars intramuralis or is covered by insulant, it is to avoid ground electrode ionizes the air that it is neighbouring, saves electric energy, improves efficiency of energy utilization；
(7) by arranging high-field electrode wire, ground electrode wire, high-field electrode line post, ground electrode line post, it is possible to simplify circuit, optimize overall structure, improve the stability and reliability run。
Accompanying drawing explanation
Fig. 1 is the fundamental diagram of dielectric barrier discharge plasma incentive structure；
Fig. 2 is the schematic three dimensional views of the embodiment of the present invention；
Fig. 3 is the side view of the embodiment of the present invention；
Fig. 4 is the top view of the embodiment of the present invention；
Fig. 5 is the partitioning plane schematic diagram of A-A position in Fig. 4；
Fig. 6 is the thrust direction schematic diagram that the embodiment of the present invention produces；
The structural representation of the integrated ground electrode of Fig. 7；
Fig. 8 is the structural representation of multiple integral ground electrode。
[symbol description]
101-shell；102-honeycomb texture；103-dielectric wall；
104-honeycomb hole；105-high-field electrode；106-ground electrode；
107-high voltage power supply；The dielectric wall of 108-outermost edges；109-insulant；
110-high-field electrode line post；111-ground electrode line post；112-high voltage power supply high-pressure side；
113-high voltage power supply earth terminal；114-dielectric；115-induced flow direction；
116-counteracting force direction；117-thrust direction；118-plasma。
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearly understand, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail。
Referring to the fundamental diagram that Fig. 1, Fig. 1 are dielectric barrier discharge plasma incentive structure。Wherein, high-field electrode 105 and ground electrode 106 interlaced arrangement are in dielectric 114 both sides, High Level AC Voltage is provided by high voltage power supply 107, high-field electrode 105 is connected with ground electrode 106 and is ionized neighbouring fluid generation plasma 118 after high-tension electricity, plasma 118 can induced flow, produce the thrust contrary with induced flow direction 115 simultaneously, thus realizing the excitation in counteracting force direction 116, simultaneously, ground electrode 106 can be covered by insulant 109, avoid ground electrode 106 to ionize neighbouring air, consume unnecessary electric power。
Refer to Fig. 2-Fig. 8, the honeycomb type dielectric barrier discharge plasma propulsion plant of first embodiment of the invention, comprising: shell 101, it is arranged at the honeycomb texture 102 in shell 101 and high voltage power supply 107, the dielectric wall 103 of this honeycomb texture forms N number of honeycomb hole 104, it is provided with M shell high-field electrode 105 along honeycomb texture axially the dielectric wall 103 in each honeycomb hole, the position that this dielectric wall 103 and M shell high-field electrode interlock is provided with M shell ground electrode 106, high-field electrode 105 and ground electrode 106 are all connected with high voltage power supply 107, wherein adjacent two layers high-field electrode 105 and ground electrode 106 form dielectric barrier discharge plasma activator, adjacent cell hole 104 shares the ground electrode 106 of its total dielectric wall, wherein, 1≤N≤1000, 1≤M≤1000。In Fig. 2 and Fig. 4, described N takes 7, and in fig. 5 and fig., described M takes 6。
Wherein, the position that the outside of the dielectric wall 108 of honeycomb texture outermost edges interlocks with M shell high-field electrode is provided with M shell ground electrode 106, the position that the inside of all the other dielectric walls interlocks with M shell high-field electrode is inlaid with M shell ground electrode 106, and adjacent cell hole 104 shares the ground electrode 106 that its total dielectric pars intramuralis is inlayed。
Preferably, the cross section of shell can be hexagon, circle, tetragon or polygon；The shape of honeycomb hole can be hexagon, triangle, tetragon or polygon。
Preferably, the material of dielectric wall is politef, quartz glass or pottery；The output voltage 500V-100kV of high voltage power supply, frequency 100Hz-100kHz, waveform are sinusoidal wave, square wave or sawtooth waveforms；The material of high-field electrode and ground electrode is copper, tungsten, molybdenum or rustless steel。
Preferably, in each honeycomb hole, every layer of high-field electrode is connected as a single entity, make to be formed in each honeycomb hole the annular high voltage electrode that M shell is identical with honeycomb hole shape, the ground electrode that adjacent dielectric wall is arranged is connected as a single entity, forming the M shell Integral grounding electrode with N number of honeycomb hole as shown in Figure 7, the annular high voltage electrode identical with honeycomb hole shape with M shell in N number of honeycomb hole is corresponding。
The honeycomb type dielectric barrier discharge plasma propulsion plant of first embodiment of the invention, after high-tension electricity connected by dielectric barrier discharge plasma activator, the high-field electrode of dielectric barrier discharge plasma activator is connected the fluid near ionization and is produced plasma with ground electrode, plasma is along the axial induced flow of honeycomb texture, and produce and induced flow thrust in opposite direction, All Media barrier discharge plasma activator all produces the thrust of equidirectional, all these thrusts make a concerted effort to be formed along the axial thrust of cellular mechanisms, as seen from Figure 6, the thrust direction 117 that the honeycomb type dielectric barrier discharge plasma propulsion plant of first embodiment of the invention produces is axial along honeycomb texture。
As can be seen here, the honeycomb type dielectric barrier discharge plasma propulsion plant of first embodiment of the invention, its simple and compact for structure, low cost of manufacture；Not having moving component, response is rapid and reliability is high；By controlling voltage and the frequency of high voltage power supply, it is possible to arrange intensity and power consumption, the thrust size accurately controlling generation of plasma excitation flexibly, when it is applied to dirigible, it is possible to achieve the accurate control of dirigible movement velocity；The direction of axis direction and adjustable thrust by adjusting honeycomb texture, when it is applied to dirigible, it is possible to achieve controlling flexibly and accurately of the dirigible direction of motion；Honeycomb texture intensity is good, it is possible to adopt relatively thin materials processing, is conducive to alleviator weight；Adjacent cell hole shares the ground electrode of dielectric wall, and adopts Integral grounding electrode structure, it is possible to alleviates weight, simplify structure；Ground electrode is embedded in dielectric pars intramuralis, it is to avoid ground electrode ionizes the air that it is neighbouring, thus saving electric energy, improves efficiency of energy utilization。
The honeycomb type dielectric barrier discharge plasma propulsion plant of second embodiment of the invention, in order to reach the purpose of brief description, in above-mentioned first embodiment, any technical characteristic making same application describes all and in this, it is not necessary to repeat identical narration。
Wherein, the arranged outside of the dielectric wall 108 of honeycomb texture outermost edges has insulant 109, and the ground electrode of the arranged outside of the dielectric wall 108 of this outermost edges is covered by insulant 109。
Preferably, insulant is politef, quartz glass or pottery。
The honeycomb type dielectric barrier discharge plasma propulsion plant of second embodiment of the invention, ground electrode is covered by insulant, it is to avoid ground electrode ionizes the air that it is neighbouring, saves electric energy further, improves efficiency of energy utilization。
The honeycomb type dielectric barrier discharge plasma propulsion plant of third embodiment of the invention, in order to reach the purpose of brief description, in any of the above-described embodiment, any technical characteristic making same application describes all and in this, it is not necessary to repeat identical narration。
Referring to Fig. 2, Fig. 3, Fig. 5 and Fig. 8, it also includes high-field electrode wire, ground electrode wire and lays respectively at N number of high-field electrode line post 110 at two ends and a ground electrode line post 111 of honeycomb texture, M shell high-field electrode in each honeycomb hole is linked together by high-field electrode wire, and be connected on high-field electrode line post 110, it is then connected to high voltage power supply high-pressure side 112；M shell Integral grounding electrode is linked together by ground electrode wire, and is connected on ground electrode line post 111, is then connected to high voltage power supply earth terminal 113。
The honeycomb type dielectric barrier discharge plasma propulsion plant of third embodiment of the invention, by arranging high-field electrode wire, ground electrode wire, high-field electrode line post, ground electrode line post, circuit can be simplified, optimize total, improve the stability and reliability run。
The honeycomb type dielectric barrier discharge plasma propulsion plant of fourth embodiment of the invention, in order to reach the purpose of brief description, in any of the above-described embodiment, any technical characteristic making same application describes all and in this, it is not necessary to repeat identical narration。
It also includes solaode, and it connects high voltage power supply 107 and provides electric energy for high voltage power supply 107。
The honeycomb type dielectric barrier discharge plasma propulsion plant of fourth embodiment of the invention, when for dirigible, is provided the electric energy consumed, it is not necessary to carry fuel by solaode, it is possible to achieve the long-term of dirigible stays sky。
So far, already in connection with accompanying drawing, the present embodiment has been described in detail。According to above description, the honeycomb type dielectric barrier discharge plasma propulsion plant of the present invention should have been had and clearly recognized by those skilled in the art。
It should be noted that in accompanying drawing or description text, the implementation not illustrating or describing, it is in art form known to a person of ordinary skill in the art, is not described in detail。Additionally, the above-mentioned definition to each element is not limited in various concrete structures, shape or the mode mentioned in embodiment, it can be carried out change simply or replace by those of ordinary skill in the art, for instance:
(1) tubular construction can also select the structure of other shapes；
(2) the direction term mentioned in embodiment, for instance " on ", D score, "front", "rear", "left", "right" etc., be only the direction with reference to accompanying drawing, be not used for limiting the scope of the invention；
(3) above-described embodiment can based on the consideration of design and reliability, and the collocation that is mixed with each other uses or uses with other embodiment mix and match, and namely the technical characteristic in different embodiments can freely form more embodiment。
In sum, a kind of honeycomb type dielectric barrier discharge plasma propulsion plant of the present invention, its simple and compact for structure, low cost of manufacture；Not having moving component, response is rapid and reliability is high；By controlling voltage and the frequency of high voltage power supply, it is possible to arrange intensity and power consumption, the thrust size accurately controlling generation of plasma excitation flexibly, when it is applied to dirigible, it is possible to achieve the accurate control of dirigible movement velocity；The direction of axis direction and adjustable thrust by adjusting honeycomb texture, when it is applied to dirigible, it is possible to achieve controlling flexibly and accurately of the dirigible direction of motion；Honeycomb texture intensity is good, it is possible to adopt relatively thin materials processing, is conducive to alleviator weight；Adjacent cell hole shares the ground electrode of dielectric wall, and adopts Integral grounding electrode structure, it is possible to alleviates weight, simplify structure；Ground electrode is embedded in dielectric pars intramuralis or is covered by insulant, it is to avoid ground electrode ionizes the air that it is neighbouring, thus saving electric energy, improves efficiency of energy utilization；The electric energy consumed is provided, it is not necessary to carry fuel, it is possible to achieve the long-term of dirigible stays sky by solaode。
Particular embodiments described above; the purpose of the present invention, technical scheme and beneficial effect have been further described; it is it should be understood that; the foregoing is only specific embodiments of the invention; it is not limited to the present invention; all within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention。
Claims (10)
1. a honeycomb type dielectric barrier discharge plasma propulsion plant, it is characterised in that including: shell (101), high voltage power supply (107) and the honeycomb texture (102) being arranged in described shell, wherein,
Described honeycomb texture includes dielectric wall (103) and described dielectric wall (103) forms N number of honeycomb hole (104), it is provided with M shell high-field electrode (105) along the honeycomb texture axially described dielectric wall in each honeycomb hole, the position that described dielectric wall interlocks with described M shell high-field electrode is provided with M shell ground electrode (106), high-field electrode (105) and ground electrode (106) connect described high voltage power supply (107), wherein adjacent two layers high-field electrode (105) and ground electrode (106) composition dielectric barrier discharge plasma activator, adjacent cell hole (104) shares the ground electrode (106) of its total dielectric wall, wherein, 1≤N≤1000, 1≤M≤1000。
2. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that the position that described dielectric wall and described M shell high-field electrode interlock is provided with described M shell ground electrode (106) and specifically includes:
Position staggered with described M shell high-field electrode outside the dielectric wall of the outermost edges of described honeycomb texture is provided with described M shell ground electrode (106), and
The position that all the other dielectric pars intramuralis of described honeycomb texture interlock with described M shell high-field electrode is inlaid with described M shell ground electrode (106), and adjacent cell hole (104) share the ground electrode (106) that its total dielectric pars intramuralis is inlayed。
3. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that:
Every layer of high-field electrode in described each honeycomb hole is connected as a single entity, form the annular high voltage electrode that M shell is identical with described honeycomb hole shape, the ground electrode that adjacent dielectric wall is arranged is connected as a single entity, forming M shell and have the Integral grounding electrode of N number of honeycomb hole, the annular high voltage electrode identical with described honeycomb hole shape with the M shell in described N number of honeycomb hole is corresponding。
4. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 2, it is characterised in that:
The dielectric wall arranged outside of the outermost edges of described honeycomb texture has insulant (109), and the ground electrode of the dielectric wall arranged outside of described outermost edges is covered by described insulant (109)。
5. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 3, it is characterized in that, also include: high-field electrode wire, ground electrode wire and lay respectively at N number of high-field electrode line post (110) at two ends and ground electrode line post (111) of described honeycomb texture；
Wherein, described M shell high-field electrode in described each honeycomb hole is linked together by described high-field electrode wire, and it is connected to described high-field electrode line post (110), it is then connected to high voltage power supply high-pressure side (112), M shell is had the Integral grounding electrode of N number of honeycomb hole and links together by described ground electrode wire, and it is connected to described ground electrode line post (111), it is then connected to high voltage power supply earth terminal (113)。
6. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that also include: solaode, it connects described high voltage power supply (107) and is that described high voltage power supply (107) provides electric energy。
7. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that: the cross section of described shell is hexagon, circle, tetragon or other polygons；And/or described honeycomb hole be shaped as hexagon, triangle, tetragon or other polygons。
8. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that described dielectric wall and insulant are politef, quartz glass or ceramic material。
9. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that the output waveform of described high voltage power supply is sinusoidal wave, square wave or sawtooth waveforms。
10. honeycomb type dielectric barrier discharge plasma propulsion plant as claimed in claim 1, it is characterised in that the material of described high-field electrode and ground electrode is copper, tungsten, molybdenum or rustless steel。
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109831866A (en) * | 2017-11-23 | 2019-05-31 | 核工业西南物理研究院 | A kind of double rings electrode coplanar discharge plasma producing apparatus |
| CN110572924A (en) * | 2019-08-15 | 2019-12-13 | 大连理工大学 | Plasma system for rolling fruit and vegetable surface microorganism control |
| CN111298974A (en) * | 2020-03-23 | 2020-06-19 | 长沙恒辉环保科技发展有限公司 | Dielectric barrier discharge's concatenation formula honeycomb electric field structure |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101511146A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Zero mass jet flow exciter of medium countercheck discharging plasma |
| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| CN102162644A (en) * | 2010-02-24 | 2011-08-24 | 中国科学院工程热物理研究所 | Dielectric barrier discharge plasma swirling device |
| CN202823134U (en) * | 2012-10-25 | 2013-03-27 | 无锡天惠塑机有限公司 | Honeycomb type waste gas purifying and recovering device |
| CN103485992A (en) * | 2013-10-14 | 2014-01-01 | 上海交通大学 | Controllable plasma propulsion device working under atmospheric pressure |
| US9137883B2 (en) * | 2013-05-24 | 2015-09-15 | National Institute Of Aerospace Associates | Robust, flexible and lightweight dielectric barrier discharge actuators using nanofoams/aerogels |
-
2016
- 2016-02-29 CN CN201610111571.1A patent/CN105704901B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101511146A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Zero mass jet flow exciter of medium countercheck discharging plasma |
| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| CN102162644A (en) * | 2010-02-24 | 2011-08-24 | 中国科学院工程热物理研究所 | Dielectric barrier discharge plasma swirling device |
| CN202823134U (en) * | 2012-10-25 | 2013-03-27 | 无锡天惠塑机有限公司 | Honeycomb type waste gas purifying and recovering device |
| US9137883B2 (en) * | 2013-05-24 | 2015-09-15 | National Institute Of Aerospace Associates | Robust, flexible and lightweight dielectric barrier discharge actuators using nanofoams/aerogels |
| CN103485992A (en) * | 2013-10-14 | 2014-01-01 | 上海交通大学 | Controllable plasma propulsion device working under atmospheric pressure |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109831866A (en) * | 2017-11-23 | 2019-05-31 | 核工业西南物理研究院 | A kind of double rings electrode coplanar discharge plasma producing apparatus |
| CN109831866B (en) * | 2017-11-23 | 2023-10-20 | 核工业西南物理研究院 | Double-ring electrode coplanar discharge plasma generating device |
| CN110572924A (en) * | 2019-08-15 | 2019-12-13 | 大连理工大学 | Plasma system for rolling fruit and vegetable surface microorganism control |
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| CN111298974A (en) * | 2020-03-23 | 2020-06-19 | 长沙恒辉环保科技发展有限公司 | Dielectric barrier discharge's concatenation formula honeycomb electric field structure |
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