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    Mitigating shock using plasma
    5.
    发明授权
    Mitigating shock using plasma 有权

    公开(公告)号：US09725159B2

    公开(公告)日：2017-08-08

    申请号：US14936953

    申请日：2015-11-10

    申请人： The Boeing Company

    发明人： Mark Joseph Clemen, Jr. ,  Donald V. Drouin, Jr. ,  Alan F. Stewart

    IPC分类号： B64C23/00 ,  B64C21/00

    CPC分类号： B64C21/00 ,  B64C23/00 ,  B64C23/005 ,  B64C30/00 ,  B64C2230/12

    摘要： 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.

    DISTRIBUTED ELECTRIC DUCTED FAN WING
    6.
    发明申请
    DISTRIBUTED ELECTRIC DUCTED FAN WING 审中-公开

    公开(公告)号：US20170190436A1

    公开(公告)日：2017-07-06

    申请号：US15374771

    申请日：2016-12-09

    申请人： David G. Ullman ,  Vincent Homer

    发明人： David G. Ullman ,  Vincent Homer

    IPC分类号： B64D27/24 ,  B64D29/02 ,  B64C3/32 ,  B64C3/44 ,  B64D31/06

    CPC分类号： B64D27/24 ,  B64C3/32 ,  B64C21/00 ,  B64D29/02 ,  B64D31/06 ,  Y02T50/166 ,  Y02T50/44 ,  Y02T50/64

    摘要： The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft.

    Plasma optimized aerostructures for efficient flow control
    7.
    发明授权
    Plasma optimized aerostructures for efficient flow control 有权
    等离子体优化航空结构，实现有效的流量控制

    公开(公告)号：US09541106B1

    公开(公告)日：2017-01-10

    申请号：US11710750

    申请日：2007-02-26

    申请人： Mehul Patel ,  Thomas Corke ,  Alan B. Cain

    发明人： Mehul Patel ,  Thomas Corke ,  Alan B. Cain

    IPC分类号： B64C29/00 ,  F15D1/00 ,  B64C21/00

    CPC分类号： F15D1/0065 ,  B64C15/14 ,  B64C21/00 ,  B64C2230/12 ,  F15D1/0075 ,  Y02T50/166

    摘要： 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.

    摘要翻译： 本发明涉及一种设计或优化用于控制飞机，导弹，弹药或汽车的等离子体致动器的控制表面的方法，更具体地涉及使用等离子致动器来控制流过其表面或其它表面的流体，这将有利于 从这样的方法。 各种实施例提供了增加飞机，导弹，弹药和汽车的效率的步骤。 流量控制方法还为减少飞机，导弹，弹药和汽车的电力需求提供了手段。 这些方法还提供了使用低功率无铰链等离子体致动器装置的空气动力学控制的替代方法。

    OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES
    8.
    发明申请
    OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES 审中-公开
    具有光电导电叶片的光学窗系统

    公开(公告)号：US20160009360A1

    公开(公告)日：2016-01-14

    申请号：US14330493

    申请日：2014-07-14

    申请人： Raytheon Company

    发明人： David A. Vasquez ,  Michael Ushinsky ,  Joseph J. Ichkhan

    IPC分类号： B64C1/14 ,  B32B37/30 ,  H05B3/84

    CPC分类号： B64C1/1484 ,  B32B37/30 ,  B64C1/1492 ,  B64C21/00 ,  B64C23/06 ,  B64C2230/10 ,  B64D47/08 ,  F42B10/46 ,  F42B15/34 ,  H05B3/84 ,  Y02T50/162 ,  Y02T50/166

    摘要： A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

    摘要翻译： 本文描述了改善在流体流动中操作并且具有第一和第二透光材料的光学窗口的光学特性的方法，每个光学透镜材料具有彼此相邻，平行并且至少部分共同延伸的边缘。 该方法包括在导光材料的第一和第二窗玻璃的两个相邻边缘之间插入导热叶片; 以及通过将导热叶片从光学窗口的窗格的外表面突出到流体流中来提升光学窗口向前的不利的流动停滞区域。

    AIRFOIL ASSEMBLY AND METHOD
    9.
    发明申请
    AIRFOIL ASSEMBLY AND METHOD 审中-公开
    气翼组件和方法

    公开(公告)号：US20150232172A1

    公开(公告)日：2015-08-20

    申请号：US14185804

    申请日：2014-02-20

    申请人： Donald Steve Morris

    发明人： Donald Steve Morris

    IPC分类号： B64C21/00 ,  B64C5/02

    CPC分类号： B64C21/00 ,  B64C23/005 ,  Y02T50/166

    摘要： Airfoil assemblies and methods of using them are provided to accelerate air flow relative to the airfoil assemblies and to improve laminar air flow over airfoils. The airfoil may include a cathode disposed near a leading portion of the airfoil to ionize on rushing air and for initiating an electric field. An anode disposed near an opposite portion of the airfoil completes the electric field to accelerate ionized air flowing relative to the airfoil, whereby ionized positively charged air particles tend to separate and accelerate continuously toward the anode in a substantially smooth laminar path of travel uninterruptedly. An air ionizing antenna may be employed for radiating an electromagnetic field transversely to the electric field to cause the electromagnetic field to ionize additional air flowing relative to the airfoil.

    摘要翻译： 提供翼型组件和使用它们的方法以加速相对于翼型组件的空气流动并且改善翼型件上的层流空气流动。 翼型件可以包括设置在翼型件的引导部分附近的阴极，以在冲刷空气中离子化并且用于启动电场。 设置在翼型件的相对部分附近的阳极完成电场以加速相对于翼型流动的电离空气，由此离子化的​​带正电的空气颗粒趋向于以不间断的基本平滑的层流路径朝向阳极分离和加速。 可以使用空气电离天线来辐射横向于电场的电磁场，以使电磁场离开相对于翼型流动的附加空气。

    Airfoil system for cruising flight
    10.
    发明授权
    Airfoil system for cruising flight 有权
    用于巡航飞行的翼型系统

    公开(公告)号：US08882049B2

    公开(公告)日：2014-11-11

    申请号：US12138709

    申请日：2008-06-13

    申请人： Qamar A. Shams ,  Tianshu Liu

    发明人： Qamar A. Shams ,  Tianshu Liu

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

    CPC分类号： B64C21/10 ,  B64C21/00 ,  B64C23/005 ,  B64C23/04 ,  B64C23/06 ,  Y02T50/162 ,  Y02T50/166

    摘要： An airfoil system includes an airfoil body and at least one flexible strip. The airfoil body has a top surface and a bottom surface, a chord length, a span, and a maximum thickness. Each flexible strip is attached along at least one edge thereof to either the top or bottom surface of the airfoil body. The flexible strip has a spanwise length that is a function of the airfoil body's span, a chordwise width that is a function of the airfoil body's chord length, and a thickness that is a function of the airfoil body's maximum thickness.

    摘要翻译： 翼型系统包括翼型体和至少一个柔性条。 翼型本体具有顶表面和底表面，弦长，跨度和最大厚度。 每个柔性带沿其至少一个边缘连接到翼型件本体的顶表面或底表面。 柔性条具有翼展长度，其为翼型体的跨度的函数，翼弦宽度为翼型本体的弦长的函数，以及作为翼型本体最大厚度的函数的厚度。