| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Wingless hovering of micro air vehicle | US13720773 | 2012-12-19 | US08960595B2 | 2015-02-24 | Subrata Roy |
| Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | ||||||
| 82 | Voltage application device, rotation apparatus and voltage application method | US13420648 | 2012-03-15 | US08937799B2 | 2015-01-20 | 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. | ||||||
| 83 | Systems and methods for controlling flows with pulsed discharges | US13523761 | 2012-06-14 | US08727286B2 | 2014-05-20 | Joseph S. Silkey; Philip Smereczniak |
| Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators. | ||||||
| 84 | WINGLESS HOVERING OF MICRO AIR VEHICLE | US13720773 | 2012-12-19 | US20130134263A1 | 2013-05-30 | SUBRATA ROY |
| Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | ||||||
| 85 | Wingless hovering of micro air vehicle | US12342583 | 2008-12-23 | US08382029B2 | 2013-02-26 | Subrata Roy |
| Embodiments relate to a Wingless Hovering Micro Air Vehicle and its Power Source Unit. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | ||||||
| 86 | SYSTEMS AND METHODS FOR CONTROLLING FLOWS WITH PULSED DISCHARGES | US13523761 | 2012-06-14 | US20130001368A1 | 2013-01-03 | Joseph S. Silkey; Philip Smereczniak |
| Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along, a surface of an it vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators. | ||||||
| 87 | AIRFLOW CONTROL DEVICE AND AIRFLOW CONTROL METHOD | US13419211 | 2012-03-13 | US20120291874A1 | 2012-11-22 | Motofumi Tanaka; Hisashi Matsuda; Hiroyuki Yasui; Shohei Goshima; Naohiko Shimura; Kunihiko Wada; Tamon Ozaki; Toshiki Osako; Masahiro Asayama; Yutaka Uchida |
| An airflow control device 10 in an embodiment includes: a vortex shedding structure portion 20 discharging an airflow flowing on a surface in a flow direction as a vortex flow; and a first electrode 40 and a second electrode 41 disposed on a downstream side of the vortex shedding structure portion 20 via a dielectric. By applying a voltage between the first electrode 40 and the second electrode 41, flow of the airflow on the downstream side of the vortex shedding structure portion 20 is controlled. | ||||||
| 88 | VOLTAGE APPLICATION DEVICE, ROTATION APPARATUS AND VOLTAGE APPLICATION METHOD | US13420648 | 2012-03-15 | US20120287550A1 | 2012-11-15 | 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. | ||||||
| 89 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft | US11519770 | 2006-09-13 | US08308112B2 | 2012-11-13 | Tommie L. Wood; Thomas C. Corke; Martiqua Post |
| 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. | ||||||
| 90 | Plasma Actuated Vortex Generators | US13073549 | 2011-03-28 | US20120248072A1 | 2012-10-04 | 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. | ||||||
| 91 | Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators | US13094872 | 2011-04-27 | US08267355B1 | 2012-09-18 | Mehul Patel; Thomas C. Corke |
| A method of controlling 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 and or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices. | ||||||
| 92 | System and method for reducing viscous force between a fluid and a surface | US12330138 | 2008-12-08 | US08240609B2 | 2012-08-14 | Claudio G. Parazzoli; Minas H. Tanielian; Robert B. Greegor |
| A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absolute value of the magnetic permeability of the metamaterial is substantially greater than an absolute value of an electric permittivity of the metamaterial. The metamaterial may generate a repulsive force between the surface and the fluid moving relative to the surface and thereby reduce viscous drag of the fluid on the surface. A method of reducing the viscous drag of the fluid moving past the surface includes producing relative motion between the surface and the fluid and generating the repulsive force between the surface and the fluid. | ||||||
| 93 | Systems and methods for controlling flows with pulsed discharges | US12339674 | 2008-12-19 | US08220753B2 | 2012-07-17 | Joseph S. Silkey; Philip Smereczniak |
| Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface. In another embodiment, high energy electrons can be injected into the boundary layer using a hollow cathode array at the airflow surface. In still another embodiment, energy can be introduced at the surface of the air vehicle at a rate sufficient to heat the flow and cause shock waves to propagate into the flow. | ||||||
| 94 | PLASMA ACTUATOR | US13391848 | 2010-08-23 | US20120152198A1 | 2012-06-21 | Yoonho Kim; Takeshi Serizawa; Akira Nakajima |
| A plasma actuator (1) includes four electrodes (11) and three dielectrics (10) and is disposed on the side of an object surface (B). When a high voltage is applied to the electrodes (11), a plasma (15) is generated at an end (10a) of each dielectric (10) exposed so as to be accessible to a gas. In the plasma actuator (1), the electrodes (11) and dielectrics (10) are alternately stacked one on another. The plasma actuator (1) includes a stepped exposed portion (X). The plasma actuator (1) in which the electrodes (11) and dielectrics (10) are arranged such that the ends (10a) of the dielectrics (10) are exposed in the normal line direction of the object surface (B) in the stacked order in the stepped exposed portion (X) can suppress the flow of the generated plasma even when the plasma actuator is exposed to a high-speed airflow under high pressure. This stabilizes the plasma. | ||||||
| 95 | Methods and apparatus for reducing drag via a plasma actuator | US11934272 | 2007-11-02 | US08091950B2 | 2012-01-10 | Thomas C. Corke; Richard Spivey |
| A vehicle includes a surface over which airflow passes. A plasma actuator is configured to generate 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 airflow from a surface of the vehicle includes generating plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma. | ||||||
| 96 | Rotary wing system with ion field flow control | US11960126 | 2007-12-19 | US08091836B2 | 2012-01-10 | Alan B. Minick |
| A rotary-wing system which generates a directed ion field to propel a fluid along a rotary-wing to control at least one boundary layer characteristic. | ||||||
| 97 | Laminated Plasma Actuator | US12762562 | 2010-04-19 | US20110253842A1 | 2011-10-20 | 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. | ||||||
| 98 | SYSTEMS AND METHODS FOR PLASMA JETS | US12968695 | 2010-12-15 | US20110089835A1 | 2011-04-21 | 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. | ||||||
| 99 | Electromagnetic flow control, methods and uses | US12100890 | 2008-04-10 | US07907038B2 | 2011-03-15 | Frank K. Lu; Donald R. Wilson; J. Craig Dutton |
| Actuation for control of surfaces is provided through use of a conducting material comprising electrolyte particles electrically charged with electromagnetic fields in boundary layers. Interactions of the electrically charged particles with electromagnetic fields in boundary layers are coordinated for generation of control forces for various applications. | ||||||
| 100 | SYSTEM & METHOD FOR REDUCING VISCOUS FORCE BETWEEN A FLUID AND A SURFACE | US12330138 | 2008-12-08 | US20100326534A1 | 2010-12-30 | Claudio G. Parazzoli; Minas H. Tanielian; Robert B. Greegor |
| A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absolute value of the magnetic permeability of the metamaterial is substantially greater than an absolute value of an electric permittivity of the metamaterial. The metamaterial may generate a repulsive force between the surface and the fluid moving relative to the surface and thereby reduce viscous drag of the fluid on the surface. A method of reducing the viscous drag of the fluid moving past the surface includes producing relative motion between the surface and the fluid and generating the repulsive force between the surface and the fluid. | ||||||
QQ群二维码
意见反馈
意见反馈