CN113944606A - Graphene-coated wire-airfoil electrode ionic wind solid-state propulsion system - Google Patents
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- CN113944606A CN113944606A CN202111212717.9A CN202111212717A CN113944606A CN 113944606 A CN113944606 A CN 113944606A CN 202111212717 A CN202111212717 A CN 202111212717A CN 113944606 A CN113944606 A CN 113944606A
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 41
- 229910021389 graphene Inorganic materials 0.000 title claims abstract description 36
- -1 graphite alkene Chemical class 0.000 claims description 11
- 239000007787 solid Substances 0.000 claims description 10
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 8
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 8
- 239000011888 foil Substances 0.000 claims description 5
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 229910002804 graphite Inorganic materials 0.000 claims description 4
- 239000010439 graphite Substances 0.000 claims description 4
- 241001669680 Dormitator maculatus Species 0.000 claims description 3
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 230000006872 improvement Effects 0.000 description 7
- 238000002474 experimental method Methods 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 238000005259 measurement Methods 0.000 description 5
- 239000002245 particle Substances 0.000 description 5
- 238000009413 insulation Methods 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- 230000005684 electric field Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000004809 Teflon Substances 0.000 description 2
- 229920006362 Teflon® Polymers 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000011889 copper foil Substances 0.000 description 2
- 239000006260 foam Substances 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 229920006934 PMI Polymers 0.000 description 1
- 238000004887 air purification Methods 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 239000007772 electrode material Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000005431 greenhouse gas Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Images
Classifications
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- 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
- F03H1/0037—Electrostatic ion thrusters
- F03H1/005—Electrostatic ion thrusters using field emission, e.g. Field Emission Electric Propulsion [FEEP]
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The invention belongs to the technical field of high-voltage plasma science, and discloses a graphene-coated wire-wing electrode ionic wind solid-state propulsion system which comprises a wire electrode, a wing electrode, an insulating frame and a high-voltage power supply, wherein the wing electrode is fixed on the insulating frame, the wire electrode and the wing electrode are arranged in parallel at intervals, the wire electrode and the wing electrode are both coated with graphene, the wire electrode is connected with a high-voltage positive output end of the high-voltage power supply, the wing electrode is connected with a high-voltage negative output end of the high-voltage power supply, the number of the wire electrode and the wing electrode is the same and is not less than 2, and the wire electrode and the wing electrode are arranged in a one-to-one correspondence manner. The invention has the beneficial effects that: the device has the advantages of simple structure, simplicity in preparation, convenience in later maintenance, low working noise, low carbon emission, high output thrust and the like, and is suitable for small and miniature aircrafts.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of high-voltage plasma science, in particular to a graphene-coated wire-wing type electrode ionic wind solid-state propulsion system.
[ background of the invention ]
In the field of aviation propulsion, conventional screw and turbine propulsion systems rely on fuel combustion to obtain a source of power. While consuming a large amount of energy, inevitably causes noise pollution, greenhouse gas emission and other influences; and the energy utilization rate is lower, and the obtained thrust power ratio is also lower. The ion wind solid-state propulsion system utilizes corona discharge to generate ion wind thrust, and has the following remarkable characteristics compared with the traditional aviation propulsion system: low working noise, easy miniaturization, low carbon and even no carbon emission. Therefore, under the national 'double-carbon' strategic guidance, the research on the high-thrust ion wind solid-state propulsion system has very important strategic significance for developing a novel aviation propulsion system and energy structure transformation in the field of power-assisted aviation propulsion.
When the asymmetric electrode corona discharges, the generated charged particles are accelerated under the action of an electric field to move and collide with air molecules to generate air jet flow, namely, ion wind. The development of ion wind has been widely studied and applied in the fields of heat dissipation enhancement, air purification, pneumatic fluid control, propulsion and the like. In recent years, graphene has attracted attention in the fields of new materials, new energy sources, and the like due to its excellent electrical and thermal conductivity. Therefore, it is necessary to provide a graphene-coated wire-airfoil electrode ion wind solid-state propulsion system, which enables a small micro aircraft to achieve low noise pollution and low carbon emission flight operation by loading the propulsion system.
[ summary of the invention ]
The invention discloses a graphene-coated wire-airfoil electrode ionic wind solid-state propulsion system, which can effectively solve the technical problems related to the background technology.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the utility model provides a solid-state propulsion system of wire-wing type electrode ion wind of coating graphite alkene, includes wire electrode, wing type electrode, insulating frame and high voltage power supply, wing type electrode is fixed on the insulating frame, the wire electrode with the parallel interval of wing type electrode sets up, the wire electrode with the wing type electrode all coats and has graphite alkene, the wire electrode with high voltage power supply's the anodal output of high pressure is connected, wing type electrode with high voltage power supply's high pressure negative output is connected.
As a preferred improvement of the present invention: the number of the lead electrodes is the same as that of the airfoil electrodes, and the lead electrodes and the airfoil electrodes are not less than 2 and are arranged in a one-to-one correspondence mode.
As a preferred improvement of the present invention: the number of the lead electrodes and the number of the airfoil electrodes are 8, the airfoil electrodes are divided into two rows along the horizontal direction, each row is divided into four rows along the vertical direction, and the airfoil electrodes are arranged in parallel.
As a preferred improvement of the present invention: the ion wind solid state propulsion system further comprises a fixing plate, wherein the fixing plate is assembled on the airfoil electrodes and is used for fixing the distance between the airfoil electrodes.
As a preferred improvement of the present invention: the ion wind solid-state propulsion system further comprises an insulating support used for isolating the lead electrode and the wing-shaped electrode, one end of the insulating support is connected with the wing-shaped electrode, and the other end of the insulating support is connected with the lead electrode.
As a preferred improvement of the present invention: the plurality of lead electrodes are connected in parallel with a high-voltage output terminal of the high-voltage power supply.
As a preferred improvement of the present invention: and a polytetrafluoroethylene rod for tightening the lead electrode is arranged on the insulating frame, and the lead electrode is fixed on the polytetrafluoroethylene rod.
As a preferred improvement of the present invention: the airfoil electrode is NACA 0010-shaped aluminum foil-coated PMI foam.
The invention has the following beneficial effects:
1. the invention aims to design a graphene-coated wire-wing type electrode ionic wind solid-state propulsion system, which has the advantages of low working noise, low carbon emission, large output thrust and the like, is suitable for small micro aircrafts, and adopts a wire-wing type electrode array structure, and compared with the wire-cylindrical electrode structure of the existing ionic wind exciter, the wing type electrode is aluminum foil PMI-coated foam, so that the weight is lighter, the flight resistance can be effectively reduced, and the stable flight of the aircrafts is facilitated; secondly, compared with the existing ionic wind exciter, the lead-airfoil electrode array coated with graphene generates more intense corona discharge and larger corona current under the same applied voltage, and the propulsion system generates larger thrust under the same condition;
2. the core of the invention is a graphene-coated lead-airfoil electrode array, and the electrode array has a simple structure, is easy to prepare and is convenient for later maintenance;
3. the invention is mostly used for small and micro aircrafts at present, but has super strong expansibility, and can be further applied to medium and large unmanned aircrafts.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without inventive efforts, wherein:
FIG. 1 is a schematic structural diagram of a graphene-coated wire-airfoil electrode ion wind solid state propulsion system according to the present invention;
FIG. 2 is a schematic view of the assembly of the polytetrafluoroethylene rod of the present invention.
In the figure: 1-lead electrode, 2-airfoil electrode, 3-fixing plate, 4-insulating support, 5-insulating frame and 6-polytetrafluoroethylene rod.
[ detailed description ] embodiments
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the following embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Referring to fig. 1-2, the present invention provides a graphene-coated wire-airfoil electrode ion wind solid-state propulsion system, which includes a wire electrode 1, an airfoil electrode 2, a fixing plate 3, an insulating support 4, an insulating frame 5, a teflon rod 6, a wire electrode interface, an airfoil electrode interface, and a high voltage power supply. Insulating frame 5 quantity is 2, is made by the foam, is located electrode array both sides, insulating frame 5 is equipped with a plurality of wing type grooves, and the wing type groove is used for the fixed wing type electrode 2 of laying coating graphite alkene. The polytetrafluoroethylene rod 6 is inserted into the insulating frame 5 through a hole, and is used for tightening the lead electrode 1 coated with graphene. The front end of the fixing plate 3 is opened, and the surface of the fixing plate is pasted with a conductive copper foil, so that the fixing plate has two main functions, namely, the fixing plate is used for fixing the distance between the airfoil electrodes 2; and secondly, the conductive copper foil is in good contact with the surface of the airfoil electrode 2 so as to connect the airfoil electrodes 2 in parallel. The insulation support 4 is in an arch shape, the rear end opening of the insulation support is fixed on the rear edge of the airfoil electrode 2, the front end of the insulation support 4 is punched and penetrates into the lead electrode 1, the insulation support 4 is used for isolating the lead electrode 1 and the airfoil electrode 2, and the phenomenon that the space between the lead and the airfoil electrode is too close to generate air breakdown when the propulsion system works is prevented. One end of the wire electrode interface is connected with each graphene-coated wire electrode 1 in parallel, and the other end of the wire electrode interface is connected with the high-voltage anode output end of the high-voltage power supply. One end of the airfoil electrode interface is connected with the airfoil electrode 2 coated with graphene in parallel, and the other end of the airfoil electrode interface is connected to a high-voltage negative electrode output end of a high-voltage power supply. The airfoil electrode 2 is made of PMI foam coated with aluminum foil in the shape of NACA0010, so that the weight is lighter, the flight resistance can be effectively reduced, and the stable flight of an aircraft is facilitated; secondly, compared with the existing ionic wind exciter, the lead-airfoil electrode array coated with graphene generates more intense corona discharge and larger corona current under the same applied voltage, and the propulsion system generates larger thrust under the same condition.
Furthermore, the lead electrode 1 is wound and fixed on the polytetrafluoroethylene rod 6 in parallel, and the middle part of the lead electrode is led out to a lead electrode interface. The airfoil electrode 2 is fixed in parallel through the fixing plate 3, and the middle part of the airfoil electrode is led out to an airfoil electrode interface. The high-voltage power supply connected with the propulsion system is a light-weight high-voltage direct-current power supply, and the wing-shaped electrode interface is connected with the high-voltage negative electrode output end of the high-voltage power supply.
Preferably, the number of the lead electrodes 1 and the number of the airfoil electrodes 2 are the same and are not less than 2, and the lead electrodes 1 and the airfoil electrodes 2 are arranged in a one-to-one correspondence manner. In this embodiment, the number of the lead electrodes 1 and the number of the airfoil electrodes 2 are 8, the airfoil electrodes 2 are divided into two rows along the horizontal direction, each row is divided into four rows along the vertical direction, and the airfoil electrodes 2 are arranged in parallel.
The method adopts the ionic wind thrust measuring platform to carry out the measurement experiment of the magnitude of the generated thrust, utilizes a balance weight measuring method to indirectly measure the thrust, and obtains the generated ionic wind thrust value through the conversion of the difference value of the scale indexes before and after the experiment. During experimental measurement, corona voltage is measured by a high-voltage probe of a polaris, corona current is measured by a current transformer, charges are recorded by adopting a capacitor carried by a power supply, and consumed power is obtained by calculating the area of a Lissajous figure. The measurement process comprises the following steps: step 1, preparing a graphene solution and uniformly stirring. Cleaning the surfaces of the lead electrode 1 and the airfoil electrode 2, immersing the surfaces in a graphene solution for soaking for half a minute, and finally putting the surfaces in an oven for drying for half an hour; the lead-foil electrode array is assembled using the fixing plate 3, the insulating support 4, the insulating frame 5, and the teflon rod 6. And 2, checking each experimental device before the experiment begins, and ensuring that the experimental device is intact and in a non-working state. And 3, arranging a lead-airfoil electrode array, connecting and fixing lead-out leads of the interfaces of the lead electrode 1 and the airfoil electrode 2 with a high-voltage positive output end and a high-voltage negative output end of a power supply respectively, and checking and confirming that the wiring is correct. And 4, opening a switch of the measuring balance, horizontally suspending the lead-airfoil electrode array below the measuring balance in the middle, and recording the initial reading of the balance. And 5, after the pretreatment is finished, turning on a high-voltage power supply to perform a corona discharge experiment, wherein the experiment voltage is increased gradually from zero to top by taking 1kV as a unit. And 6, recording readings of stable and timed measurement days after each boosting, and measuring a plurality of groups of data analysis average values. And 7, after the experiment is finished, removing the high-voltage power supply and the measuring balance, taking down the lead-wing electrode array, and placing the lead-wing electrode array in a dry place.
The parameters of the wire-airfoil electrode material can be changed at will, and the content of graphene in the graphene solution and the thickness of the coating of the graphene coating can be changed at will. In the embodiment, the lead electrode 1 is a bare copper lead with a diameter of 0.2mm, and the airfoil electrode 2 adopts a U.S. NACA series standard shape NACA 0010. The content of graphene in the graphene solution is 5%, and the thickness of the coating is controlled to be about 0.02 mm. The high-pressure laboratory for experimental measurement has the air pressure of standard atmospheric pressure, the temperature of 20-25 ℃ and the relative humidity of air of 50-60%. The experimental result shows that when the applied voltage is 40kV, the corona current measured by the current measuring resistor is 14.8mA, and the thrust obtained by converting the reading of the measuring balance is 3.25N. Under the same condition, the output thrust is increased by about 10 percent compared with the wire-airfoil electrode array which is not coated with graphene.
The working principle is as follows: the principle that the asymmetric electrode generates ion wind under atmospheric pressure through corona discharge is utilized, the lead-airfoil electrode is the asymmetric electrode, the graphene material has high length-width ratio and conductivity, and the characteristic enables the graphene material to be used as the electrode with smaller curvature radius to be attached to the surface of the lead electrode 1, so that a stronger non-uniform electric field is formed around the lead electrode 1, secondary electron emission around the electrode is enhanced, and corona onset voltage is reduced. The lead electrode 1 is connected with the positive output end of the high-voltage power supply and ionizes neutral particles of air nearby the lead electrode into charged particles. The charged particles are accelerated under the action of coulomb force of an electric field between the wire and the airfoil electrode, and transfer momentum to the neutral particles through collision, thereby causing jet flow of air, namely ion wind. The reaction force of the ion wind acting on the airfoil electrode 2 is the ion wind thrust, and can be used for aircraft propulsion. According to the invention, the wire-airfoil electrode array coated with graphene is used for generating and utilizing ion wind thrust to provide propulsion power for an aircraft.
While embodiments of the invention have been disclosed above, it is not limited to the applications set forth in the specification and the embodiments, which are fully applicable to various fields of endeavor for which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (8)
1. A graphene-coated wire-airfoil electrode ionic wind solid state propulsion system is characterized in that: including wire electrode (1), airfoil electrode (2), insulating frame (5) and high voltage power supply, airfoil electrode (2) are fixed on insulating frame (5), wire electrode (1) with airfoil electrode (2) parallel interval sets up, wire electrode (1) with airfoil electrode (2) all are coated with graphite alkene, wire electrode (1) with high voltage power supply's the anodal output of high voltage power supply is connected, airfoil electrode (2) with high voltage power supply's high-pressure negative pole output is connected.
2. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 1, wherein: the number of the lead electrodes (1) is the same as that of the airfoil electrodes (2), and the lead electrodes (1) are not less than 2, and the airfoil electrodes (2) are arranged in a one-to-one correspondence manner.
3. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 2, wherein: the number of the lead electrodes (1) and the number of the airfoil electrodes (2) are 8, the airfoil electrodes (2) are divided into two rows along the horizontal direction, each row is divided into four rows along the vertical direction, and the airfoil electrodes (2) are arranged in parallel.
4. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 2, wherein: the ion wind solid-state propulsion system further comprises a fixing plate (3), wherein the fixing plate (3) is assembled on the airfoil electrodes (2) and is used for fixing the distance between the airfoil electrodes (2).
5. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 1, wherein: the ion wind solid-state propulsion system further comprises an insulating support (4) used for isolating the lead electrode (1) and the wing-shaped electrode (2), one end of the insulating support (4) is connected with the wing-shaped electrode (2), and the other opposite end of the insulating support is connected with the lead electrode (1).
6. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 2, wherein: the plurality of lead electrodes (1) are connected with a high-voltage output end of the high-voltage power supply in a parallel mode.
7. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 1, wherein: and a polytetrafluoroethylene rod (6) for tightening the lead electrode (1) is arranged on the insulating frame (5), and the lead electrode (1) is fixed on the polytetrafluoroethylene rod (6).
8. The graphene coated wire-airfoil electrode ionic wind solid state propulsion system of claim 1, wherein: the airfoil electrode (2) is NACA 0010-shaped PMI foam coated with aluminum foil.
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| CN202111212717.9A CN113944606A (en) | 2021-10-18 | 2021-10-18 | Graphene-coated wire-airfoil electrode ionic wind solid-state propulsion system |
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| CN202111212717.9A CN113944606A (en) | 2021-10-18 | 2021-10-18 | Graphene-coated wire-airfoil electrode ionic wind solid-state propulsion system |
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|---|---|---|---|---|
| US20080197779A1 (en) * | 2007-02-16 | 2008-08-21 | Timothy Scott Fisher | Various methods, apparatuses, and systems that use ionic wind to affect heat transfer |
| CN109860382A (en) * | 2019-01-30 | 2019-06-07 | 江苏大学 | A kind of integrated form ion wind for power-type LED heat dissipation is heat sink |
| KR102023898B1 (en) * | 2019-05-09 | 2019-09-23 | 김철 | Flight vehicle for electric dust collector using thrust force and ionic wind |
| CN111591451A (en) * | 2020-04-27 | 2020-08-28 | 泉州信息工程学院 | Ionic wind propelled airplane and propelling method thereof |
| CN111885900A (en) * | 2020-08-24 | 2020-11-03 | 广东工业大学 | Annular LED ionic wind heat abstractor |
| US20210039112A1 (en) * | 2018-04-07 | 2021-02-11 | Praful Ramachandra Naik | An air purification system |
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2021
- 2021-10-18 CN CN202111212717.9A patent/CN113944606A/en active Pending
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|---|---|---|---|---|
| US20080197779A1 (en) * | 2007-02-16 | 2008-08-21 | Timothy Scott Fisher | Various methods, apparatuses, and systems that use ionic wind to affect heat transfer |
| US20210039112A1 (en) * | 2018-04-07 | 2021-02-11 | Praful Ramachandra Naik | An air purification system |
| CN109860382A (en) * | 2019-01-30 | 2019-06-07 | 江苏大学 | A kind of integrated form ion wind for power-type LED heat dissipation is heat sink |
| KR102023898B1 (en) * | 2019-05-09 | 2019-09-23 | 김철 | Flight vehicle for electric dust collector using thrust force and ionic wind |
| CN111591451A (en) * | 2020-04-27 | 2020-08-28 | 泉州信息工程学院 | Ionic wind propelled airplane and propelling method thereof |
| CN111885900A (en) * | 2020-08-24 | 2020-11-03 | 广东工业大学 | Annular LED ionic wind heat abstractor |
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| Title |
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| HAOFENG XU: "Flight of an aeroplane with solid-state propulsion", 《NATURE》 * |
| 欧阳芳相等: "离子风飞机推进电极阵列的推力影响因素", 《中国电机工程学报》 * |
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Application publication date: 20220118 |