| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Multi-electromagnetic tile for the boundary layer control | JP51103194 | 1993-06-25 | JPH08503433A | 1996-04-16 | ノーセンチュック，ダニエル，エム．; ブラウン，ゲリイ，エル． |
| The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall (100) of a body is controlled by generating in the fluid a magnetic field B &cir& NOt (103) having flux lines parallel to the surface of the wall and an electric current density J &cir& NOt (109) traversing the magnetic flux lines in the fluid to form a control region. An electrolyte or other conductivity-enhancing material (13) is introduced into the flow to provide a conductivity gradient in the fluid flow in the near-wall region. The magnetic field B &cir& NOt (103) and the electric current density J &cir& NOt (109) create in the control region a force J &cir& NOt X B &cir& NOt (131) having a component normal to the surface of the wall that because of the conductivity gradient in the fluid flow near the surface can stabilize or destabilize flow in the boundary layer. A plurality of such control regions are arranged in an array of control tiles that can be individually actuated to reduce the power required to provide boundary layer control over a given area. | ||||||
| 62 | 플라즈마를 이용하여 충격을 완화시키기 위한 방법 및 장치 | KR1020160116981 | 2016-09-12 | KR1020170054979A | 2017-05-18 | 마크조셉클레멘,쥬니어; 도날드브이.드루인,쥬니어; 알란에프.스튜어트 |
| 차량에대한임계마하수보다큰 속도로주행하는차량의바람직하지않은효과를완화시키기위한방법, 장치및 시스템. 자외선에너지는, 차량에대한임계마하수보다큰 속도로주행하는차량의내부구조와연결된복수의자외선에너지소스를이용하여발생된다. 자외선에너지는, 차량의선택된위치주위로차량의외부를지나복수의자외선에너지소스로부터이송된다. 플라즈마는, 차량에대한임계마하수보다큰 속도로주행하는차량의바람직하지않은효과를완화시키기위해선택된위치의주위에생성된다. | ||||||
| 63 | 3가지 관련 기능을 가진 전자 컴포넌트 | KR1020107005006 | 2008-03-03 | KR1020100063711A | 2010-06-11 | 빼리숑끌로드아니; 기리프랑스와; 부엔디아호세; 삐까뤼가피에르 |
| Electronic component which modifies, by electronic re-equilibration, mechanical efficiencies, audio-visual effects, and food products. The electronic component eCRT is a regulator which, like entropy, regulates the exchanges of natural equilibrium of the information of electro-magnetic charges with electronic charges. This equilibrium is to naturally clean the air and the excess of magnetic charges around apparatus or in inert products that have accumulated non-useful electrons which are then absorbed, attracted captured by the trap of the metallic components. Nanotechnology makes it possible to see the migration of the magnetic fields converted into electric current whose piezo is fed in order to vibrate. These functions are all natural but, associated together, they create novel functions specific to this method. This vision of nano-technology makes it possible to solve, on a large scale, invisible solutions, through a vision of suitable scale. The application to sound in ambient space of the eCRT electronic component is the supreme demonstration of the audio magnetic loss captured by the piezo-electricity eCRT which captures the magnetic field instantaneously and transforms the magnetic information into electric current, according to the audio modulation. This audio electrical modulation by the thirst, the transience of the piezoelectricity is transformed into audible mechanical motion of the sound lost initially by the coil. | ||||||
| 64 | 수직 이착륙 항공기의 날개, 나셀 및/또는 동체에 항력감소를 위한 플라즈마 액튜에이터 | KR1020087009113 | 2006-08-17 | KR1020080058405A | 2008-06-25 | 우드,토미; 코크,토마스씨.; 포스트,마르티카 |
| An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma. | ||||||
| 65 | 풍력 발전 터빈의 회전익 날개 | KR1020057004432 | 2003-09-16 | KR100669036B1 | 2007-01-16 | 워벤알로이즈 |
| 본 발명은 회전익 날개, 특히 풍력 발전 설비의 회전익 날개에 관한 것이다. 본 발명의 목적은 풍력 발전 설비의 회전익 날개의 공기 저항 계수를 개선하고 음향 전력 레벨을 낮추기 위함이다. 본 발명에 따른 풍력 발전 설비의 회전익 날개는 가압면과 흡입면을 구비하고, 상기 흡입면 상에 균일하고 전체를 커버하는 정전계가 인가됨을 특징으로 한다. 풍력발전, 회전익 날개, 로터 블레이드, 동전기. | ||||||
| 66 | 풍력 발전 터빈의 회전익 날개 | KR1020057004432 | 2003-09-16 | KR1020050057340A | 2005-06-16 | 워벤알로이즈 |
| The invention relates to a rotor blade, particularly a rotor blade of a wind power plant. The aim of the invention is to provide measures with which the CW value (drag coefficient) as well as the sound power level of rotor blades of wind power plants can be even further improved. The inventive rotor blade for a wind power plant has a delivery side and an induction side, whereby an essentially constant overall electrostatic field is formed on the induction side. | ||||||
| 67 | CYCLOTRONIC PLASMA ACTUATOR WITH ARC-MAGNET FOR ACTIVE FLOW CONTROL | US16387777 | 2019-04-18 | US20190246482A1 | 2019-08-08 | Joseph W. Zimmerman; David L. Carroll; Phillip J. Ansell; Georgi Hristov |
| In an embodiment of the invention there is a cyclotronic actuator utilizing a high-voltage plasma driver connected to a first electrode. A second electrode is grounded and the two are isolated from each other by a dielectric plate. A magnet is positioned beneath the dielectric plate such that a coaxial dielectric barrier discharge plasma is formed outwardly between the first electrode across the dielectric plate. The magnet positioned beneath the dielectric plate introduces a magnetic field transverse to the plasma current path, such that the plasma discharge discharges radially and the local magnetic field is oriented vertically in a direction perpendicular to the dielectric plate to create a Lorentz Force, which forces the plasma discharge to move radially outwardly in a curved radial streamer mode pattern. | ||||||
| 68 | ICE DETECTION/PROTECTION AND FLOW CONTROL SYSTEM BASED ON PRINTING OF DIELECTRIC BARRIER DISCHARGE SLIDING PLASMA ACTUATORS | US16301969 | 2017-09-25 | US20190193863A1 | 2019-06-27 | Mohammadmahdi ABDOLLAHZADEHSANGROUDI; Jose Carlos PASCOA MARQUES; Frederico Miguel FREIRE RODRIGUES |
| The present invention relates to an ice detection/protection and flow control system based on printing of dielectric barrier discharge sliding plasma actuators. This invention has advantages such as: reduced weight, low maintenance cost, no environmental impact, fully electric operation and combination of functionalities (ice detection, deicing, anti-icing and flow control).The system comprises the following components: exposed AC electrode (1), dielectric layer (2), embedded electrode (3), sliding/nanosecond electrode (4), ground plane (5), AC power supply (6), DC power supply (7), nanosecond range pulse generator (8), monitoring capacitor (9), high voltage probe (10), control module (11), temperature sensor (12), control signal input module (13) and monitoring system (14). The system senses ice formation and generates extensive surface heating to prevent ice accumulation. | ||||||
| 69 | Method and system for generating plasma in an atmosphere | US15331183 | 2016-10-21 | US10117319B2 | 2018-10-30 | Reginald J Exton |
| A method is provided for generating a region of plasma in a gaseous atmosphere that includes argon. A laser beam from a Ti:sapphire laser is directed into the gaseous atmosphere such that a portion of the argon along the laser beam is ionized. Microwave energy is directed into the ionized region of the laser beam to generate a plasma. | ||||||
| 70 | Laminated plasma actuator | US12762562 | 2010-04-19 | US09975625B2 | 2018-05-22 | Joseph Steven Silkey; David James Suiter; Bradley Alan Osborne |
| A method and apparatus may comprise a first number of layers of a flexible material, a second number of layers of a dielectric material, a first electrode attached to a surface layer in the first number of layers, and a second electrode attached to a second layer in one of the first number of layers and the second number of layers. The first number of layers may be interspersed with the second number of layers. The first electrode may be configured to be exposed to air. The first electrode and the second electrode may be configured to form a plasma in response to a voltage. | ||||||
| 71 | Method of increasing the performance of aircraft, missiles, munitions and ground vehicles with plasma actuators | US13570684 | 2012-08-09 | US09834301B1 | 2017-12-05 | Mehul Patel; Tom Corke |
| A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices. | ||||||
| 72 | FLUID MACHINE WITH PLASMA ACTUATOR | US15667720 | 2017-08-03 | US20170326989A1 | 2017-11-16 | Takehiko SEGAWA; Takayuki MATSUNUMA; Timothy JUKES |
| A fluid machine includes a rotary blade, a casing configured to house the rotary blade therein, and an insulation coated conductor attached within a recess circumferentially provided in an inner circumference of the casing opposed to an outer end of the rotary blade, the insulation coated conductor including a conductive wire and an insulation material coating. The dielectric barrier discharge is generated between the insulation coated conductor and the outer end of the rotary blade by applying a pulse voltage between the conductive wire and the rotary blade, so as to prevent leakage of operative fluid through a tip clearance between the inner circumference of the casing and the outer end of the rotary blade. | ||||||
| 73 | Voltage application device, rotation apparatus and voltage application method | US14503462 | 2014-10-01 | US09644632B2 | 2017-05-09 | Motofumi Tanaka; Hisashi Matsuda; Shohei Goshima; Hiroyuki Yasui; Amane Majima; Toshiki Osako |
| A voltage application device of an embodiment applies a voltage between a first and second electrode disposed separately from each other in an airflow generation device, which is disposed on a rotation blade of a rotation apparatus, in which a rotation shaft of the rotation blade is held rotatably by a holding part. In the voltage application device of the embodiment, a voltage output unit outputs a voltage. Then, a sliding type transmission unit having electrodes disposed respectively on the rotation blade side and the holding part side of the rotation shaft transmits a voltage outputted from the voltage output unit from the holding part side to the rotation blade side. Then, a transformation unit disposed on the rotation blade side increases the voltage transmitted by the sliding type transmission unit and outputs the voltage to the airflow generation device. | ||||||
| 74 | Plasma-assisted synthetic jets for active air flow control | US14186760 | 2014-02-21 | US09637224B2 | 2017-05-02 | Dejan Nikic |
| A plasma-assisted synthetic jet device, an aircraft including a plasma-assisted synthetic jet device, and a method of improving aerodynamic properties are disclosed for providing air flow control at an aerodynamic structure by ionizing one or more gases exiting through an aperture of the synthetic jet device disposed in the aerodynamic structure. | ||||||
| 75 | EMBEDDED DIELECTRIC STRUCTURES FOR ACTIVE FLOW CONTROL PLASMA SOURCES | US14864796 | 2015-09-24 | US20170088255A1 | 2017-03-30 | Dejan Nikic |
| An aircraft active flow control dielectric barrier discharge (DBD) device may include a machinable ceramic dielectric support having an aerodynamic surface shaped to form an exposed flush part of an airfoil surface on an aircraft. The DBD device may include at least two electrodes configured to be oppositely charged and spaced apart from each other on the dielectric support. | ||||||
| 76 | MICROELECTRONIC MODULE, MODULE ARRAY, AND METHOD FOR INFLUENCING A FLOW | US15233495 | 2016-08-10 | US20170043863A1 | 2017-02-16 | Ralf CASPARI; Robert WEICHWALD; Emanuel ERMANN; Karin BAUER |
| A microelectronic module for influencing a flow of a fluid is provided. The module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one active flow-influencing element for influencing the direction and/or the speed of a fluid which is flowing around and/or over the flow-influencing element. At least the voltage converter and the active flow-influencing element are disposed on a thin-film, planar substrate. The influencing of the direction and/or the speed of the fluid is dependent on a hydrodynamic acceleration as a function of the second voltage provided by the voltage converter at the flow-influencing element. | ||||||
| 77 | Method of processing acoustic waves emitted at the outlet of a turbo engine of an aircraft with a dielectric-barrier discharge device and aircraft comprising such a device | US13643382 | 2011-04-18 | US09361876B2 | 2016-06-07 | Alexandre Alfred Gaston Vuillemin |
| A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discharge device so as to emit an electric wind in a direction of acoustic waves so as to attenuate the acoustic waves. An aircraft can include such a dielectric barrier discharge device. | ||||||
| 78 | Laser-Based Flow Modification to Remotely Control Air Vehicle Flight Path | US14460984 | 2014-08-15 | US20150307184A1 | 2015-10-29 | Kevin Kremeyer |
| Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance. | ||||||
| 79 | MULTIFUNCTIONAL EROSION PROTECTION STRIP | US14646050 | 2013-11-20 | US20150298791A1 | 2015-10-22 | Pontus Nordin; Göte Strindberg |
| An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system. | ||||||
| 80 | PLASMA-ASSISTED SYNTHETIC JETS FOR ACTIVE AIR FLOW CONTROL | US14186760 | 2014-02-21 | US20150239552A1 | 2015-08-27 | Dejan Nikic |
| A plasma-assisted synthetic jet device, an aircraft including a plasma-assisted synthetic jet device, and a method of improving aerodynamic properties are disclosed for providing air flow control at an aerodynamic structure by ionizing one or more gases exiting through an aperture of the synthetic jet device disposed in the aerodynamic structure. | ||||||
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