| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Systems and methods for plasma jets | US11018708 | 2004-12-20 | US07183515B2 | 2007-02-27 | Daniel N. Miller; Paul D. McClure; Charles J. Chase; Robert R. Boyd |
| A plasma jet system includes a housing with an 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. | ||||||
| 162 | Systems and methods for plasma jets | US11018708 | 2004-12-20 | US20060131282A1 | 2006-06-22 | Daniel Miller; Paul McClure; Charles Chase; Robert Boyd |
| A plasma jet system includes a housing with an 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. | ||||||
| 163 | Turbulent flow drag reduction | US10474008 | 2002-03-26 | US07017863B2 | 2006-03-28 | Simon J Scott; Graham A Johnson; Edward Thornton |
| The present invention relates to apparatus for influencing fluid flow over a surface, and more particularly, but not exclusively, to turbulent boundary layer flow drag reduction for an aircraft. The present invention provides such apparatus including a plasma generator comprising first and second spaced-apart independently controllable electrodes operable to cause a change in direction of the flow of the fluid over the surface. | ||||||
| 164 | Surface plasma discharge for controlling leading edge contamination and crossflow instabilities for laminar flow | US10406940 | 2003-04-03 | US06805325B1 | 2004-10-19 | Norman Malmuth; Alexander Fedorov |
| The present invention provides a system and method for controlling leading edge contamination and crossflow instabilities for laminar flow on aircraft airfoils that is lightweight, low power, economical and reliable. Plasma surface discharges supply volumetric heating of the supersonic boundary layers to control the Poll Reynolds number and the cross flow Reynolds number and delay transition to turbulent flow associated with the leading edge contamination and crossflow instabilities. A closed-loop feedback control system that incorporates these principles includes three primary components: heat-flow sensors, a PID controller, and plasma discharge elements. Heat-flow sensors distributed around the airfoil surface provide root-mean-square (rms) pulsations of the heat flow to the airfoil skin. These data are fed to the PID controller to determine the flow state (laminar or turbulent) and to drive voltage inputs to the plasma discharge elements, which provide the volumetric heating of the boundary layer on a time scale necessary to adapt to changing flight conditions and delay transition to turbulent flow. | ||||||
| 165 | Turbulent flow drag reduction | US10474008 | 2003-10-09 | US20040200932A1 | 2004-10-14 | Simon J. Scott; Graham A. Johnson; Edward Thornton |
| The present invention relates to apparatus for influencing fluid flow over a surface, and more particularly, but not exclusively, to turbulent boundary layer flow drag reduction for an aircraft. The present invention provides such apparatus including a plasma generator comprising first and second spaced-apart independently controllable electrodes operable to cause a change in direction of the flow of the fluid over the surface. | ||||||
| 166 | Surface plasma discharge for controlling forebody vortex asymmetry | US10326751 | 2002-12-20 | US06796532B2 | 2004-09-28 | Norman D. Malmuth; Alexander Fedorov; Vladimir Shalaev; Vladimir Zharov; Ivan Shalaev; Anatoly Maslov; Victor Soloviev |
| The present invention provides a system and method for rapidly and precisely controlling vortex symmetry or asymmetry on aircraft forebodies to avoid yaw departure or provide supplemental lateral control beyond that available from the vertical tail surfaces with much less power, obtrusion, weight and mechanical complexity than current techniques. This is accomplished with a plasma discharge to manipulate the boundary layer and the angular locations of its separation points in cross flow planes to control the symmetry or asymmetry of the vortex pattern. Pressure data is fed to a PID controller to calculate and drive voltage inputs to the plasma discharge elements, which provide the volumetric heating of the boundary layer on a time scale necessary to adapt to changing flight conditions and control the symmetry or asymmetry of the pressures and vortices. In the case of yaw departure avoidance, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide a robustly stable symmetric vortex pattern on a time scale that the asymmetries develop. In the case of lateral control, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide an asymmetric vortex pattern that produces the desired supplementary lateral force and rolling moment. | ||||||
| 167 | Method for generating surface plasma | US10061408 | 2002-01-31 | US06570333B1 | 2003-05-27 | Paul A. Miller; Ben P. Aragon |
| A method for generating a discharge plasma which covers a surface of a body in a gas at pressures from 0.01 Torr to atmospheric pressure, by applying a radio frequency power with frequencies between approximately 1 MHz and 10 GHz across a plurality of paired insulated conductors on the surface. At these frequencies, an arc-less, non-filamentary plasma can be generated to affect the drag characteristics of vehicles moving through the gas. The plasma can also be used as a source in plasma reactors for chemical reaction operations. | ||||||
| 168 | Method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators | US10104914 | 2002-03-22 | US20020195526A1 | 2002-12-26 | Ronald M. Barrett; Christopher Reasonover; Jeremy Corpening |
| A method and apparatus for active boundary layer control on an aerodynamic surface. One or more piezoelectric synthetic jet actuators operate as a boundary layer pump to ingest fluid along the surface of an aerodynamic object and discharge fluid tangentially to the fluid flow along the surface and/or at the trailing edge of the object to reduce drag and delay stall. | ||||||
| 169 | System for supplying power to ROSAR transponders, including transmitting and receiving antennas for ROSAR devices | US10050894 | 2002-01-18 | US20020109356A1 | 2002-08-15 | Helmut Klausing; Horst Kaltschmidt |
| In a system for supplying power to ROSAR transmitting and receiving antennas that are integrated into the tip of a helicopter rotor blade, wind energy is converted directly into electrical energy locally at the rotor blade tip. | ||||||
| 170 | Method and apparatus for cleaning surfaces with a glow discharge plasma at one atmosphere of pressure | US458136 | 1995-06-02 | US5938854A | 1999-08-17 | John Reece Roth |
| The surface of a workpiece is cleaned by generating a steady-state one atmosphere glow discharge plasma above the surface of the workpiece. The use of one atmosphere, uniform glow discharge plasmas generated by a low frequency RF ion trapping mechanisms is preferred. The plasma used to effect surface cleaning may be formed in atmospheric air or other gases at about one atmosphere of pressure, or at pressures below or above one atmosphere. | ||||||
| 171 | Micro-electrode and magnet array for microturbulence control | US846899 | 1997-05-01 | US5934622A | 1999-08-10 | James C. S. Meng |
| A boundary layer control device for a surface which reduces turbulence by oviding forces which counteract microturbulent events occurring at the surface. The microturbulent events occur periodically with a known topography and include liftup and ejection, bursting, low-speed streak and sweep topography. The device has an array of magnet and electrode cells which are arranged to correspond with the topography arrangement of the microturbulent events. The interaction of the magnetic and electric fields within the cells generate a Lorentz force which can be directed into or out of the surface depending on the relative directions of the magnetic and electric fields. Sensors on the surface determine which cells to activate and in what direction to apply the Lorentz force to precisely counteract the microturbulent events occurring at the surface. A force directed away from the surface is used to counteract a sweep event and a force directed towards the surface counteracts a liftup event. No force is applied during low-speed streak events. | ||||||
| 172 | Method and apparatus for reducing the drag of flows over surfaces | US659306 | 1996-06-06 | US5803409A | 1998-09-08 | Laurence R. Keefe |
| An apparatus, and its accompanying method, for reducing the drag of flows over a surface includes arrays of small disks and sensors. The arrays are embedded in the surface and may extend above, or be depressed below, the surface, provided they remain hydraulically smooth either when operating or when inactive. The disks are arranged in arrays of various shapes, and spaced according to the cruising speed of the vehicle on which the arrays are installed. For drag reduction at speeds of the order of 30 meters/second, preferred embodiments include disks that are 0.2 millimeter in diameter and spaced 0.4 millimeter apart. For drag reduction at speeds of the order of 300 meters/second, preferred embodiments include disks that are 0.045 millimeter in diameter and spaced 0.09 millimeter apart. Smaller and larger dimensions for diameter and spacing are also possible. The disks rotate in the plane of the surface, with their rotation axis substantially perpendicular to the surface. The rotating disks produce velocity perturbations parallel to the surface in the overlying boundary layer. The sensors sense the flow at the surface and connect to control circuitry that adjusts the rotation rates and duty cycles of the disks accordingly. Suction and blowing holes can be interspersed among, or made coaxial with, the disks for creating general three-component velocity perturbations in the near-surface region. The surface can be a flat, planar surface or a nonplanar surface, such as a triangular riblet surface. The present apparatus and method have potential applications in the field of aeronautics for improving performance and efficiency of commercial and military aircraft, and in other industries where drag is an obstacle, including gas and oil delivery through long-haul pipelines. | ||||||
| 173 | Surface layer comprising micro-fabricated tiles for electromagnetic control of fluid turbulence in sea water | US668031 | 1996-06-14 | US5791275A | 1998-08-11 | Promode R. Bandyopadhyay |
| A surface layer for use in connection with an object adapted for motion tugh a fluid includes an array of tiles each having a pair of electrodes and a pair of magnetic poles positioned to generate respective electric and magnetic fields generally transverse to each other. Either or both of the electrodes or magnetic poles are controllable to provide adjustable electrical and/or controllable magnetic fields. A plurality of turbulence sensors is provided each located proximate to and generally upstream of a tile. Each turbulence sensor generating a turbulence signal representative of fluid turbulence proximate thereto. A control circuit for controlling the electrical field generated by the electrodes and/or the magnetic field generated by the magnetic pole in relation to the turbulence signal from the turbulence sensors, thereby to generate a Lorentz force for controlling the fluid. The length and time scales of the electro-magnetic tiles can be matched to those of near-wall turbulence in high Reynolds number flows. The tiles can be fabricated using silicon micro-fabrication or printed circuit board techniques, which provides for cost-effective fabrication and ensures relatively lightweight and reduced energy requirements. Due to their smallness, plurality and amenability, digital microprocessor technology with appropriate algorithm maybe used to control near-wall turbulence. | ||||||
| 174 | Multiple electromagnetic tiles for boundary layer control | US169599 | 1993-12-17 | US5437421A | 1995-08-01 | Daniel M. Nosenchuck; Garry L. Brown |
| The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in the fluid a magnetic field B having flux lines along the surface of the wall and an electric current density J traversing the magnetic flux lines in the fluid to form a control region. The magnetic field B and the electric current density J create in the control region a force J.times.B that can stabilize or destabilize flow in the boundary layer. A plurality of such control regions can be arranged in an two-dimensional array of control tiles that are periodically actuated in a controlled, predetermined pattern at a critical frequency that provides boundary layer control over a given area. | ||||||
| 175 | Electromagnetic device and method for boundary layer control | US986257 | 1992-12-07 | US5320309A | 1994-06-14 | Daniel M. Nosenchuck; Garry L. Brown |
| The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in a near-wall region of the flow a magnetic field B having flux lines parallel to the surface of the wall and an electric current density J traversing the magnetic flux lines in the fluid. An electrolyte or other conductivity-enhancing material is introduced into the flow to provide an electrical conductivity gradient in the near-wall region. The magnetic field B and the electric current density J create in the fluid a force J.times.B having a component normal to the surface of the wall that because of the increased conductivity gradient near the surface can stabilize or destabilize flow in the boundary layer. Numerous aspects of the fluid flow and its interaction with the body can thus be controlled. As examples, shear stress in the fluid at the wall can be decreased, with a corresponding reduction in viscous drag, the characteristics of the acoustic and pressure fields in the fluid surrounding the body can be controlled to reduce noise and fatigue, and boundary layer separation can be inhibited or induced. | ||||||
| 176 | Device for reducing the supersonic boom caused by aircraft | US3655147D | 1968-04-25 | US3655147A | 1972-04-11 | PREUSS HEINZ |
| The invention describes means for reducing the supersonic boom caused by aircraft. Underneath the aircraft reflecting surfaces are provided in the area of the maximum pressure difference of the Mach cone created by the aircraft.
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| 177 | Airfoil fluid flow control system | US50056455 | 1955-04-11 | US2946541A | 1960-07-26 | BOYD JOHN R |
| 178 | Laser-based flow modification to remotely control air vehicle flight path | US15359047 | 2016-11-22 | US10124883B2 | 2018-11-13 | 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. | ||||||
| 179 | Plasma control and power system | US12983205 | 2010-12-31 | US10011344B1 | 2018-07-03 | Edmund J. Santavicca, Jr.; Srikanth Vasudevan; Frederick J. Lisy; Mike Ward |
| An improved high-voltage AC power supply energizes and regulates plasma actuators for aerodynamic flow control. Such plasma actuators are used, for example, on aerodynamic surfaces, wind turbine blades, and the like for vehicle control, drag or noise reduction, or efficient power generation. Various embodiments of the power supply are small, compact, lightweight, portable, modular, self-contained in its own housing, easily replaceable and swappable, autonomous, self-cooling, and/or gangable in series or parallel to provide any desired control authority over the selected surface. In some embodiments, the parameters for the plasma electronics can be manually selected and pre-programmed for a specific application, while in preferred embodiments, the plasma electronics can automatically identify the appropriate parameters and self-tune the performance of the plasma actuators. | ||||||
| 180 | METHOD AND APPARATUS OF PLASMA FLOW CONTROL FOR DRAG REDUCTION | US15662040 | 2017-07-27 | US20180031013A1 | 2018-02-01 | Thomas C. Corke; Flint O. Thomas |
| A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow. | ||||||
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