| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Method and apparatus for providing high control authority atmospheric plasma | US14770347 | 2014-02-25 | US09820369B2 | 2017-11-14 | Subrata Roy |
| Embodiments of the invention relate to a method and apparatus for providing high thrust density plasma, and/or high control authority plasma. In specific embodiments, such high thrust density, and/or high control authority, plasma can be at or near atmospheric pressure. Embodiments pertain to a method and apparatus that use electron confinement via one or more magnetic fields, and/or one or more electric fields, in a manner to improve the ionization due to surface plasma actuators. Specific embodiments can improve ionization by several orders of magnitude. This improved ionization can result in a high electric field inside the sheath for the same applied voltage and can result in very high thrust. | ||||||
| 182 | Laser-Based Flow Modification to Remotely Control Air Vehicle Flight Path | US15359047 | 2016-11-22 | US20170291694A1 | 2017-10-12 | 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. | ||||||
| 183 | Mitigating Shock Using Plasma | US14936953 | 2015-11-10 | US20170129592A1 | 2017-05-11 | Mark Joseph Clemen, JR.; Donald V. Drouin, JR.; Alan F. Stewart |
| A method, apparatus, and system for mitigating undesired effects of a vehicle traveling at a speed greater than a critical Mach number for the vehicle. Ultraviolet energy is generated using a plurality of ultraviolet energy sources associated with an interior structure of the vehicle that travels at the speed greater than the critical Mach number for the vehicle. The ultraviolet energy is transported from the plurality of ultraviolet energy sources past an exterior of the vehicle around a selected location of the vehicle. A plasma is created around the selected location to mitigate the undesired effects of the vehicle traveling at the speed greater than the critical Mach number for the vehicle. | ||||||
| 184 | Laser-based flow modification to remotely control air vehicle flight path | US14460984 | 2014-08-15 | US09533753B2 | 2017-01-03 | 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. | ||||||
| 185 | Systems and methods for alleviating aircraft loads with plasma actuators | US12166199 | 2008-07-01 | US09446840B2 | 2016-09-20 | Donald V. Drouin, Jr.; Scott Lee Schwimley |
| Systems and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft component structural response to an aerodynamic load. The method can further include, based at least in part on the input corresponding to the aircraft component's structural response, reducing the structural response to the aerodynamic load by activating at least one plasma actuator carried by the aircraft, in accordance with one or more activation parameters. | ||||||
| 186 | Gas turbine engines having plasma flow-controlled intake systems | US13898275 | 2013-05-20 | US09359950B2 | 2016-06-07 | Mark Matwey |
| Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure. | ||||||
| 187 | A POROUS COATING APPLIED ONTO AN AERIAL ARTICLE | US14439929 | 2012-10-31 | US20150292074A1 | 2015-10-15 | Pontus Nordin; Per Hallander; Jonas Bohlin; Thomas Hellstrom |
| An aerial article including a composite skin, a leading edge facing an airflow during use of the aerial article, an erosion resistant coating including a metallic material, and an aerodynamic surface. The coating at least partly covers the composite skin of the aerial article. The coating has a porosity sufficiently high to provide an open area, diffusion passage way, so as to permit moisture transportation from the composite skin to the aerodynamic surface of the coating. A method of applying an erosion resistant coating including a metallic material to a composite skin of an aerial article. An erosion resistant coating material is provided onto the composite skin over a selected area of the article. The coating is porous. The outer surface of the coating is polished to achieve a smooth aerodynamic surface. | ||||||
| 188 | SURFACE PLASMA ACTUATOR | US14420015 | 2013-06-24 | US20150267727A1 | 2015-09-24 | Takehiko Segawa; Takayuki Matsunuma; Timothy Jukes |
| A surface plasma actuator includes a conducting wire attached to a surface of a target object and electrically insulated from the target object. Surface plasma is generated along a neighborhood of the conducting wire by applying a pulse voltage between the conducting wire and a conductive portion on a side of the target object. An induced gas flow is generated by the surface plasma. | ||||||
| 189 | Plasma-enhanced active laminar flow actuator system | US13821196 | 2010-09-15 | US09067674B2 | 2015-06-30 | Pontus Nordin; Göte Strindberg |
| The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano-engineered composite material layer (5) comprising a set of electrodes arranged (7′, 7″) in at least an upper (P1) and a lower (P2) plane extending parallel with the aerodynamic surface (3); the electrodes (7′, 7″) comprising nano filaments (9); the electrodes (7′) of the upper plane (P1) are arranged in the aerodynamic surface (3) such that they define a smooth and hard aerodynamic surface (3); conductors (11, 11′) of nano filaments (9″) arranged for electrical communication between a control unit (13) and each of the electrodes (7′, 7″), wherein the control unit (13) is adapted to address current between cooperating electrodes (7′, 7″) of the upper and lower plane (P1, P2) from a current supply depending upon air flow characteristic signals fed from air flow sensor means (19). | ||||||
| 190 | Boundary layer flow disruptors for delaying transition to turbulent flow | US13937494 | 2013-07-09 | US08939410B2 | 2015-01-27 | Reginald J Exton |
| An apparatus delays the transition of a boundary layer flow from laminar to turbulent. Flow disruptors are positioned to be in contact with a boundary layer flow moving in a flow direction over a surface. Each flow disruptor generates fluctuations in the boundary layer flow such that the frequency of the fluctuations is a damping region frequency defined by an amplification rate curve associated with the boundary layer flow. | ||||||
| 191 | Plasma actuated vortex generators | US13073549 | 2011-03-28 | US08916795B2 | 2014-12-23 | Paul D. McClure; Dennis B. Finley; Sergey Macheret |
| A plasma-actuated vortex generator arrangement includes a plurality of spaced-apart vortex generators, and a plasma actuator distributed amongst the plurality of vortex generators. | ||||||
| 192 | Laser-based flow modification to remotely control air vehicle flight path | US12289262 | 2008-10-23 | US08827211B2 | 2014-09-09 | 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. | ||||||
| 193 | BOUNDARY LAYER FLOW DISRUPTORS FOR DELAYING TRANSITION TO TURBULENT FLOW | US13937494 | 2013-07-09 | US20140217241A1 | 2014-08-07 | Reginald J Exton |
| An apparatus delays the transition of a boundary layer flow from laminar to turbulent. Flow disruptors are positioned to be in contact with a boundary layer flow moving in a flow direction over a surface. Each flow disruptor generates fluctuations in the boundary layer flow such that the frequency of the fluctuations is a damping region frequency defined by an amplification rate curve associated with the boundary layer flow. | ||||||
| 194 | Aerodynamic performance enhancements using discharge plasma actuators | US12739825 | 2008-10-26 | US08708651B2 | 2014-04-29 | David Greenblatt |
| The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing. | ||||||
| 195 | Systems and methods for plasma jets | US12968695 | 2010-12-15 | US08242404B2 | 2012-08-14 | Daniel N. Miller; Paul D. McClure; Charles J. Chase; Robert R. Boyd |
| A plasma jet system includes a housing with a single opening. A plasma generator is coupled to ionize a fluid in the housing. An electromagnetic accelerator is coupled to generate an electric field that accelerates ionized fluid in the housing toward the opening. A controller can modulate the frequency of the electric field to cause the ionized fluid to form a plasma vortex flow through the opening. A magnetic field is applied normal to the direction of the plasma vortex flow to mitigate the momentum of the electrons. The electrons slowed by the magnetic field can be collected and conducted to a location where they are re-inserted into the plasma vortex flow to maintain charge neutrality. | ||||||
| 196 | Method and apparatus for multibarrier plasma actuated high performance flow control | US12598993 | 2008-05-08 | US08235072B2 | 2012-08-07 | Subrata Roy |
| A plasma actuator incorporates a power source, a first electrode in contact with a first dielectric layer, a second electrode in contact with a second dielectric layer, and a ground electrode. The power source drives the first electrode with a first ac voltage pattern with respect to the ground electrode to produce a first plasma discharge, and a first electric field pattern in the flow region, and drives the second electrode with a second ac voltage pattern with respect to the ground electrode to produce a second plasma discharge in the flow region and a second electric field pattern in the flow region. The first and second electrodes are offset along the direction of flow and the first voltage pattern and the second voltage pattern have a phase difference such that the first and second electric fields drive flow in different portions of the flow region at different times. | ||||||
| 197 | Plasma enhanced riblet | US12477760 | 2009-06-03 | US08220754B2 | 2012-07-17 | Paul D. McClure; Sergey Macheret; Brian R. Smith; Kurt M. Chankaya |
| An object moving through a fluid uses plasma to keep turbulent mixing vortices associated with turbulent air away from the majority of the surface of the object. The plasma may be used to enhance physical riblets, or the plasma may create a virtual riblet. | ||||||
| 198 | ELECTRONIC COMPONENT WITH THREE ASSOCIATED FUNCTIONS | US12672477 | 2008-03-03 | US20120155758A1 | 2012-06-21 | Claude Annie Perrichon; Francois Giry; Jose Buendia; Pierre Piccaluga |
| 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. | ||||||
| 199 | Method, apparatus, and system for deflecting air approaching a wing | US12262568 | 2008-10-31 | US08181910B2 | 2012-05-22 | Blair J. Lewis |
| Fluid having a velocity approaching a surface having a leading edge may be deflected. An electric field may be projected ahead of the leading edge of the surface to ionize at least some molecules of the fluid approaching the wing. The strength of the electric field may vary between a maximum level and a minimum level periodically over time. A magnetic field may be projected from the surface to deflect the ionized molecules of the fluid such that some or all of the deflection is normal to the velocity of the approaching fluid and normal to the leading edge of the surface while the electric field is below its maximum level. | ||||||
| 200 | Active directional control of airflows over rotorcraft blades using plasma actuating cascade arrays | US12432451 | 2009-04-29 | US08157528B1 | 2012-04-17 | Vyacheslav Khozikov; Shengyi Liu; George M. Roe |
| Methods of constructing plasma actuating cascade arrays for actively controlling airflow over rotorcraft blades are described herein. These methods may include providing plasma actuating cascade arrays that include dielectrics and electrodes. The electrodes and dielectrics are electrically operated to generate plasma clusters, and to induce directional airflows in response to the plasma clusters. The methods may also include configuring the plasma actuating cascade arrays based, at least in part, on characteristics of the rotorcraft blades and characteristics of flight regimes and scenarios. | ||||||
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