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    Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators
    32.
    发明授权
    Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators 有权
    用等离子执行器控制飞机，导弹，弹药和地面车辆的方法

    公开(公告)号：US07954768B1

    公开(公告)日：2011-06-07

    申请号：US12604903

    申请日：2009-10-23

    申请人： Mehul Patel ,  Thomas C. Corke

    发明人： Mehul Patel ,  Thomas C. Corke

    IPC分类号： B64C23/00 ,  B64C21/00 ,  F42B15/01

    CPC分类号： B64C23/005 ,  B62D35/007 ,  B64C2230/12 ,  F42B10/38 ,  F42B10/40 ,  F42B10/668 ,  Y02T50/166

    摘要： 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 or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.

    摘要翻译： 使用等离子体致动器控制飞机，导弹，弹药或地面车辆的方法，更具体地说是控制流过其表面或将受益于这种方法的其它表面的流体流动的方法包括设计空气动力学等离子体致动器，目的在于 控制飞机，导弹或地面车辆的控制表面上的气流分离，以及为了在这些车辆上进行流体流动控制的目的，确定等离子体致动器的调制频率的方法。 各种实施例提供了增加飞机，导弹，弹药和地面车辆的效率的步骤。 流量控制的方法降低了飞机，导弹，弹药或地面车辆的电力需求。 这些方法还提供使用低功率无铰链等离子体致动器装置的替代空气动力学控制。

    Flying Object for Transonic or Supersonic Velocities
    33.
    发明申请
    Flying Object for Transonic or Supersonic Velocities 失效
    超音速或超音速飞行对象

    公开(公告)号：US20100243818A1

    公开(公告)日：2010-09-30

    申请号：US12784611

    申请日：2010-05-21

    申请人： Erich Schülein

    发明人： Erich Schülein

    IPC分类号： B64C21/00

    CPC分类号： B64C23/04 ,  B64C21/02 ,  B64C30/00 ,  B64C2230/22 ,  Y02T50/166

    摘要： The invention relates to a flying object which moves with a transonic or supersonic velocity. The inventive flying object comprises a main body, a streaming element and a holding element. The holding element holds the streaming element distant from the main body. The streaming element is permeable for the airstream. For one embodiment the streaming element is built with a porous material. The streaming element has an outer surface with the shape of a cone or a truncated cone. The holding element holds the streaming element in an orientation with the cone opening towards the airstream.

    摘要翻译： 本发明涉及一种以跨音速或超声速度移动的飞行物体。 本发明的飞行物体包括主体，流动元件和保持元件。 保持元件保持远离主体的流动元件。 流动元件对于气流是可渗透的。 对于一个实施例，流动元件由多孔材料构成。 流动元件具有锥形或截锥形状的外表面。 保持元件将流动元件保持在朝向气流的锥形开口的方向上。

    Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft
    34.
    发明申请
    Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft 有权
    等离子致动器，用于在机翼，机舱和/或垂直起飞和着陆飞机机身上进行减阻

    公开(公告)号：US20100224733A1

    公开(公告)日：2010-09-09

    申请号：US11519770

    申请日：2006-09-13

    申请人： Tommie L. Wood ,  Thomas C. Corke ,  Martiqua Post

    发明人： Tommie L. Wood ,  Thomas C. Corke ,  Martiqua Post

    IPC分类号： B64C21/00

    CPC分类号： B64C23/005 ,  B64C2230/12 ,  F05D2270/172 ,  F15D1/12 ,  H05H1/2406 ,  Y02T50/166

    摘要： 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.

    摘要翻译： 飞机包括气流通过的表面。 等离子体致动器被配置为在表面上产生等离子体，等离子体将指向的动量耦合到围绕表面的空气中，以减少气流与表面的分离。 一种减少气流与飞行器表面的分离的方法包括在不存在等离子体的情况下在气流与表面分离的位置处在表面周围的空气中产生等离子体。

    Systems and methods for controlling flows with electrical pulses
    35.
    发明授权
    Systems and methods for controlling flows with electrical pulses 有权
    用电脉冲控制流量的系统和方法

    公开(公告)号：US07744039B2

    公开(公告)日：2010-06-29

    申请号：US11649706

    申请日：2007-01-03

    申请人： Richard B. Miles ,  Sergey O. Macheret ,  Mikhail Shneider ,  Alexandre Likhanskii ,  Joseph Steven Silkey

    发明人： Richard B. Miles ,  Sergey O. Macheret ,  Mikhail Shneider ,  Alexandre Likhanskii ,  Joseph Steven Silkey

    IPC分类号： B64C21/00

    CPC分类号： B64C23/005 ,  B64C2039/105 ,  B64C2230/12 ,  B64D15/12 ,  F05D2270/172 ,  F15D1/12 ,  H05H1/2406 ,  Y02T50/12 ,  Y02T50/166

    摘要： Systems and methods for controlling flow with electrical pulses are disclosed. An aircraft system in accordance with one embodiment includes an aerodynamic body having a flow surface exposed to an adjacent air stream, and a flow control assembly that includes a first electrode positioned at least proximate to the flow surface and a second electrode positioned proximate to and spaced apart from the first electrode. A dielectric material can be positioned between the first and second electrodes, and a controller can be coupled to at least one of the electrodes, with the controller programmed with instructions to direct air-ionizing pulses to the electrode, and provide a generally steady-state signal to the electrode during intervals between the pulses.

    摘要翻译： 公开了用电脉冲控制流量的系统和方法。 根据一个实施例的飞行器系统包括具有暴露于相邻空气流的流动表面的空气动力体，以及流动控制组件，其包括至少邻近流动表面定位的第一电极和邻近并间隔开的第二电极 除了第一个电极。 介电材料可以位于第一和第二电极之间，并且控制器可以耦合到至少一个电极，其中控制器用指令编程以将空气电离脉冲引导到电极，并且提供一般的稳态 在脉冲之间的间隔期间向电极发出信号。

    METHOD AND APPARATUS FOR MITIGATING TRAILING VORTEX WAKES OF LIFTING OR THRUST GENERATING BODIES
    38.
    发明申请
    METHOD AND APPARATUS FOR MITIGATING TRAILING VORTEX WAKES OF LIFTING OR THRUST GENERATING BODIES 审中-公开
    用于缓解提升或扭转生物体的VORTEX波浪的方法和装置

    公开(公告)号：US20080061192A1

    公开(公告)日：2008-03-13

    申请号：US11852753

    申请日：2007-09-10

    申请人： Steven Sullivan

    发明人： Steven Sullivan

    IPC分类号： B64C21/10 ,  B64C21/00 ,  B64C23/00 ,  B64C9/00 ,  B64C21/06

    CPC分类号： B64C23/005 ,  B64C21/10 ,  B64C2230/12 ,  B64C2230/26 ,  F05D2270/172 ,  Y02T50/166

    摘要： This patent provides for a method and apparatus for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface geometries promotes vortex-mixing of high and low flow fluids. The method and apparatus can be combined with various drag reduction techniques, such as the use of riblets of various types and/or compliant surfaces (passive and active). Such combinations form unique structures for various fluid dynamic control applications to suppress transiently growing forms of boundary layer disturbances in a manner that significantly improves performance and has improved control dynamics.

    摘要翻译： 该专利提供了一种用于减轻由提升或推力发生体和操纵控制表面产生的集中尾流涡流结构的形成的方法和装置，其中使用轮廓表面几何形状促进高流动和低流动流体的涡流混合。 该方法和装置可以与各种减阻技术组合，例如使用各种类型的肋和/或柔性表面（被动和主动）。 这种组合形成用于各种流体动态控制应用的独特结构，以显着改善性能并改善控制动力学的方式抑制边界层扰动的瞬时增长形式。

    Flow surface for a three-dimensional boundary-layer flow, especially on a swept wing, a swept tail plane or a rotor
    39.
    发明申请
    Flow surface for a three-dimensional boundary-layer flow, especially on a swept wing, a swept tail plane or a rotor 失效
    用于三维边界层流动的流动表面，特别是在扫掠翼，扫掠尾翼面或转子上

    公开(公告)号：US20070029450A1

    公开(公告)日：2007-02-08

    申请号：US11496760

    申请日：2006-08-01

    申请人： Markus Kloker ,  Ralf Messing

    发明人： Markus Kloker ,  Ralf Messing

    IPC分类号： B64C21/00

    CPC分类号： B64C21/06 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/22 ,  Y02T50/166

    摘要： A flow surface (16), e.g. on a swept aircraft wing, has a three-dimensional boundary-layer flow. The surface is defined by a spanwise direction (z) and a chordwise direction (x). In or on the flow surface excitation locations (22) are arranged, exciting primary disturbances. The disclosure is characterized in that the excitation locations (22) are arranged such that benign steady primary disturbances are excited and maintained on a sufficiently-high amplitude level as longitudinal vortices respectively crossflow vortices, suppressing naturally growing nocent primary disturbances by a non-linear physical mechanism. The benign primary disturbances preserve a laminar flow, such that unsteady secondary disturbances, which may initiate turbulence and which, otherwise, are excited in streamwise direction by nocent primary vortices, are suppressed or at least stabilized.

    摘要翻译： 流动表面（16） 在扫掠的飞机机翼上，具有三维边界层流。 表面由翼展方向（z）和弦向（x）定义。 在流动表面中或上面布置有激励位置（22），激发初级扰动。 本发明的特征在于，激励位置（22）被布置成使得良好的稳定主干扰被激发并保持在足够高的振幅水平上，因为纵向涡流分别横流涡流，通过非线性物理抑制自然增长的无机主干扰 机制。 良性的主要扰动保持层流，从而抑制或至少稳定了不稳定的二次扰动，其可能引发湍流，否则，通过非主要的涡流在流动方向上被激发。

    Method and apparatus using localized heating for laminar flow
    40.
    发明授权
    Method and apparatus using localized heating for laminar flow 失效
    使用局部加热进行层流的方法和装置

    公开(公告)号：US6027078A

    公开(公告)日：2000-02-22

    申请号：US32185

    申请日：1998-02-27

    申请人： Jeffrey D. Crouch ,  Lian L. Ng

    发明人： Jeffrey D. Crouch ,  Lian L. Ng

    IPC分类号： B64C21/00

    CPC分类号： B64C21/00 ,  Y02T50/166

    摘要： A method and apparatus using localized heating to encourage laminar flow along an airfoil exterior surface. The airfoil includes a leading edge (24), a controlled surface (18), and an uncontrolled surface (20). The present invention localized heating system (38) includes a heat source (40) located within the airfoil and connected to the leading edge (24), and a heat sink (42) positioned aft of the heat source (40) and arranged to transfer heat from the airfoil controlled surface (18) to the uncontrolled surface (20). The heat sink (42) preferably expels heat along uncontrolled surface adjacent to turbulent air flow. In one preferred embodiment as applied to a generally circular aircraft engine nacelle (12), the heat source (40) is an electro-thermal heat source (44) having a high resistance wire embedded in a composite material leading edge structure (50), and the heat sink (42) is a heat pipe (52) having a wicking material (58) and a vaporizing agent (60). A method of encouraging laminar flow about a controlled surface of an airfoil is further provided. The method includes heating (61) the outer surface near the leading edge region, drawing (62) heat from a controlled surface downstream of the heated surface, and expelling (63) heat along the an uncontrolled surface.

    摘要翻译： 使用局部加热以促进沿翼型外表面的层流的方法和装置。 翼型件包括前缘（24），受控表面（18）和不受控制的表面（20）。 本发明的局部加热系统（38）包括位于机翼内并连接到前缘（24）的热源（40）和位于热源（40）后面并被布置成传递的散热器 从翼型控制表面（18）到不受控制的表面（20）的热量。 散热器（42）优选地沿着与湍流空气流相邻的不受控制的表面排出热量。 在一个优选实施例中，应用于大致圆形的飞机发动机机舱（12），热源（40）是具有嵌入在复合材料前缘结构（50）中的高电阻丝的电热源（44） 并且散热器（42）是具有芯吸材料（58）和汽化剂（60）的热管（52）。 还提供了一种鼓励围绕机翼受控表面的层流的方法。 该方法包括加热（61）前缘区域附近的外表面，从加热表面下游的受控表面拉出（62）加热，并沿着不受控制的表面排出（63）热量。