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    FLUIDIC CONSTRUCTS FOR ELECTRONIC DEVICES
    1.
    发明申请
    FLUIDIC CONSTRUCTS FOR ELECTRONIC DEVICES 有权
    电子设备流体结构

    公开(公告)号：US20120068801A1

    公开(公告)日：2012-03-22

    申请号：US13252695

    申请日：2011-10-04

    申请人： Amy E. Duwel ,  Jason O. Fiering ,  Douglas W. White ,  Brian R. Smith

    发明人： Amy E. Duwel ,  Jason O. Fiering ,  Douglas W. White ,  Brian R. Smith

    IPC分类号： H01F21/04

    CPC分类号： H01Q1/364 ,  H01Q3/01 ,  H01Q3/44

    摘要： In various embodiments, an inductance of an inductor is tuned by adjusting a position of a conductor and/or a magnetic material with respect to a conducting wire of the inductor, thereby changing the electro-magnetic characteristics of the conducting wire. The conductor and/or magnetic material can be disposed in a microfluidic channel and can be moved within the microfluidic channel using a suitable actuator mechanism.

    摘要翻译： 在各种实施例中，通过相对于电感器的导线调节导体和/或磁性材料的位置来调节电感器的电感，由此改变导线的电磁特性。 导体和/或磁性材料可以设置在微流体通道中并且可以使用合适的致动器机构在微流体通道内移动。

    VORTEX GENERATION DEVICE
    5.
    发明申请
    VORTEX GENERATION DEVICE 有权
    VORTEX生成装置

    公开(公告)号：US20120049001A1

    公开(公告)日：2012-03-01

    申请号：US12869884

    申请日：2010-08-27

    申请人： Brian R. Smith ,  Patrick J. Yagle

    发明人： Brian R. Smith ,  Patrick J. Yagle

    IPC分类号： B64C1/38

    CPC分类号： B64C23/06 ,  Y02T50/162

    摘要： A vortex generation device for reducing drag on an upswept aircraft fuselage afterbody and including a vortex generator vane that extends longitudinally from along an outer mold line of the fuselage of an aircraft adjacent an upswept afterbody of the fuselage and that is configured and positioned to reduce drag on an upswept aircraft fuselage afterbody by developing vortices that counteract vortices generated along such an upswept fuselage afterbody. The vane is disposed aft of a side paratrooper jump door of the aircraft fuselage and has a spine and leading end that are faired smoothly into the mold line of the fuselage.

    摘要翻译： 一种涡流发生装置，用于减少上行的飞行器机身后部的阻力，并包括涡流发生器叶片，该涡流发生器叶片沿着机身机身的外部模具线在机身的上升后身体之间纵向延伸，并且被配置和定位成减小阻力 通过开发涡流来抵抗沿着这种上升的机身后身产生的涡流，在一个上升的机身后身上。 叶片位于飞机机身的侧伞式跳伞的后方，并具有顺利进入机身模具线的脊柱和前端。

    Dual bimorph synthetic pulsator
    6.
    发明授权
    Dual bimorph synthetic pulsator 有权
    双双压缩合成波轮

    公开(公告)号：US07967258B2

    公开(公告)日：2011-06-28

    申请号：US11473676

    申请日：2006-06-23

    申请人： Brian R. Smith ,  Seyed Saddoughi

    发明人： Brian R. Smith ,  Seyed Saddoughi

    IPC分类号： B64C21/04

    CPC分类号： B64C21/08 ,  B64C2230/18 ,  F15D1/12 ,  Y02T50/166 ,  Y10T137/0318 ,  Y10T137/3584

    摘要： The present invention provides a system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a synthetic jet actuator(s) located within an ambient pressure chamber, wherein the synthetic jet actuator is operable to produce an oscillatory flow. The oscillatory flow of the synthetic jet(s) produces the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.

    摘要翻译： 本发明提供一种用于使用合成脉动器主动地操纵表面上的流体流动的系统和方法。 合成脉动器产生可操作以操纵靠近合成脉动器的主要流体流的脉冲喷射。 合成脉动器包括位于环境压力室内的合成射流致动器，其中合成射流致动器可操作以产生振荡流。 合成射流的振荡流产生可操作以操纵主流体流的脉冲射流。 然后可以主动地操纵这些合成脉动器以控制管道流体流动的流动行为，影响流体流动内的流场涡流的起始点和轨迹，并减少初级流体流中的流动分离。