| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Staggered actuation of electromagnetic tiles for boundary layer control | US751827 | 1996-11-19 | US5964433A | 1999-10-12 | Daniel M. Nosenchuck |
| 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 introduces a vorticity distribution .omega. (x,y,z,t) into the flow. A plurality of such control regions is arranged in an two-dimensional array of control tiles that are actuated such that over the array the vorticity at the wall in the direction transverse to the free-stream direction is reduced and creation of the boundary layer vorticity concentrations in the free-stream direction is inhibited. | ||||||
| 122 | System for increasing the aerodynamic and hydrodynamic efficiency of a vehicle in motion | US625914 | 1996-04-01 | US5797563A | 1998-08-25 | Ronald F. Blackburn; Barry M. Warmkessel; Sonja M. Kawamoto |
| The system includes radiation generation and transmission components which radiate tuned microwave electromagnetic energy outwardly from a vehicle through an antenna into a fluid medium through which the vehicle is moving. The microwave radiation is at the frequency of harmonic resonance electromagnetic excitation of the molecules of the medium which produces efficient heating and ionizing of the fluid resulting in a reduction of the mass density thereof. This reduction decreases the drag forces acting on the vehicle resulting in a greatly enhanced aerodynamic and/or hydrodynamic efficiency and also decreases the intensity of the shock waves (which often lead to sonic booms). An aircraft's dramatically higher speed in the surrounding rarefied medium can make it appear to be travelling at "supersonic" speeds. The system also includes a set of coiled wires and magnetic plates producing magnetic fields proximal to the vehicle and oriented to deflect heated molecules (ionized by the microwave heating) away from the vehicle thereby preventing or reducing contact of the heated molecules with the vehicle's outer surfaces and heating thereof. | ||||||
| 123 | Sonic boom attenuator | US944188 | 1992-09-11 | US5263661A | 1993-11-23 | Jennifer K. Riley |
| The Sonic Boom Attenuator is a device designed for use with supersonic aircraft wherein a laser beam is shone down the leading edge of a short, rigid, straight, thin wing, heating thus rarefying the air before it passes over and under the wing. In this manner, the compression (which results from the rarefication) occurs more slowly as the relative wind passes through the beam than it otherwise would by impact with the hard surface of the wing. Because of the simplicity of design there are fewer components than have been proposed by other inventions and fewer mechanical devices to fail. Because of the rarefication, there is an overall reduction in drag to the aircraft and an attenuation of sonic boom in supersonic flight. | ||||||
| 124 | Method and means for reducing the skin friction of bodies moving in a fluid medium | US3510094D | 1967-12-11 | US3510094A | 1970-05-05 | CLARK JAMES |
| 1,258,407. Utilizing energy of radiations. J. CLARK. 10 Dec., 1968 [11 Dec., 1967], No. 58757/68. Heading G6P. A radio-active coating is provided on the skin of aircraft in order to reduce aero-dynamic drag. The energy emission from the coating is controlled by adjustment of the electrical biasing potential. Both beta and alpha emitting coatings are employed and the energy emission from the coating to the air is effected by emission directly into the air or by the excitation of a crystal lattice at the air boundary. In some embodiments, the radio-active material is bonded to the aircraft skin and covered with alternate layers of P and N type semi-conductive layers which have an adjustable bias to control the energy of the alpha or beta emission. PN, NP, PNP, NPN and field-effect junctions may be used. Collimation of the emission is effected by a crystal lattice layer interposed between the radio-active coating and the semiconductive layers. In an alternative form, the radio-active material is alloyed with the semiconductor by ionic bombardment. | ||||||
| 125 | Air resistance reducer | US14823937 | 1937-06-14 | US2102527A | 1937-12-14 | HADLEY EVERETT M |
| 126 | ROTOR SUPPORT DEVICE, ROTOR, GAS TURBINE ENGINE, AND AIRCRAFT | US16192718 | 2018-11-15 | US20190193842A1 | 2019-06-27 | Hiroki KATO; Maki KIKUCHI |
| A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor. | ||||||
| 127 | ACTIVE FLOW CONTROL SYSTEM | US15525203 | 2015-11-19 | US20180281932A1 | 2018-10-04 | Brian E. WAKE; Claude G. MATALANIS; Patrick BOWLES |
| An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage. | ||||||
| 128 | METHOD AND SYSTEM FOR GENERATING PLASMA IN AN ATMOSPHERE | US15331183 | 2016-10-21 | US20180263103A1 | 2018-09-13 | 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. | ||||||
| 129 | Multifunctional erosion protection strip | US14646050 | 2013-11-20 | US10035578B2 | 2018-07-31 | 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. | ||||||
| 130 | ACTUATORS FOR FLOW CONTROL AT SURFACES OF AERODYNAMIC PROFILES | US15827580 | 2017-11-30 | US20180149178A1 | 2018-05-31 | Ralf CASPARI; Robert WEICHWALD; Emanuel ERMANN; Gerd HELLER; Detlev KONIGORSKI; Stefan SCHNÄUBELT; Nicole JORDAN |
| An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators. | ||||||
| 131 | Surface plasma actuator | US14420015 | 2013-06-24 | US09951800B2 | 2018-04-24 | 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. | ||||||
| 132 | Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow | US15784878 | 2017-10-16 | US20180105258A1 | 2018-04-19 | Pedro Paredes Gonzalez; MEELAN M. CHOUDHARI; FEI LI |
| A method and system delay the laminar-to-turbulent transition of a supersonic or hypersonic boundary layer flow moving in a flow direction over a surface. For supersonic boundary layer flow, oblique first-mode instability waves present in the boundary layer and propagating at an oblique angle relative to the flow direction cause a laminar-to-turbulent transition in the boundary layer flow. These instability waves have a wavelength associated therewith in a direction perpendicular to the flow direction. Flow disruptors are used to generate modulations within the boundary layer flow wherein a wavelength of the modulations along the direction perpendicular to the flow direction is less than one-half of the wavelength of the instability waves. For hypersonic boundary layer flow, the flow disruptors generate modulations within the boundary layer flow wherein the wavelength of the modulations is less than streak spacing for optimal transient growth or, equivalently, in the range of one to two times the boundary layer thickness. | ||||||
| 133 | Embedded dielectric structures for active flow control plasma sources | US14864796 | 2015-09-24 | US09771146B2 | 2017-09-26 | 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. | ||||||
| 134 | Mitigating shock using plasma | US14936953 | 2015-11-10 | US09725159B2 | 2017-08-08 | 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. | ||||||
| 135 | Plasma optimized aerostructures for efficient flow control | US11710750 | 2007-02-26 | US09541106B1 | 2017-01-10 | Mehul Patel; Thomas Corke; Alan B. Cain |
| The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices. | ||||||
| 136 | Airflow control device and airflow control method | US13419211 | 2012-03-13 | US09297260B2 | 2016-03-29 | 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. | ||||||
| 137 | METHOD AND APPARATUS FOR PROVIDING HIGH CONTROL AUTHORITY ATMOSPHERIC PLASMA | US14770347 | 2014-02-25 | US20160007436A1 | 2016-01-07 | 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. | ||||||
| 138 | DRAG REDUCTION THROUGH ION FIELD FLOW CONTROL | US14629558 | 2015-02-24 | US20150284072A1 | 2015-10-08 | Alan B. Minick; William T. Cousins |
| A method for controlling a boundary layer over a vehicle surface includes generating an ionic wind using a network of emitters and receivers. An external fluid is propelled with the ionic wind over the vehicle surface. The strength of the ionic wind is controlled to adjust the boundary layer thickness. | ||||||
| 139 | VOLTAGE APPLICATION DEVICE, ROTATION APPARATUS AND VOLTAGE APPLICATION METHOD | US14503462 | 2014-10-01 | US20150110651A1 | 2015-04-23 | Motofumi Tanaka; Hisashi Matsuda; Shohei Goshima; Hiroyuki Yasui; Amane Majima; Toshiki Osaka |
| 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. | ||||||
| 140 | Plasma actuator | US13391848 | 2010-08-23 | US08941291B2 | 2015-01-27 | 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. | ||||||
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