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    System and method to control flowfield vortices with micro-jet arrays
    1.
    发明申请
    System and method to control flowfield vortices with micro-jet arrays 有权
    用微喷射阵列控制流场涡旋的系统和方法

    公开(公告)号：US20100084514A1

    公开(公告)日：2010-04-08

    申请号：US12319585

    申请日：2009-01-09

    Applicant: Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    Inventor： Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    IPC: B64C21/04 ,  B64C19/00

    CPC classification number: B64C21/02 ,  B64C2230/18 ,  Y02T50/166

    Abstract: The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices within the fluid flow places micro-jet arrays on surfaces bounding the fluid flow. These micro-jet arrays are then 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.

    Abstract translation: 本发明提供一种用于使用微喷射阵列主动地操纵和控制在表面上的流体流动内的空气动力学或流体动力学流场涡旋的系统和方法。 用于主动操纵和控制流体流动内的流场旋涡的起始点，大小和轨迹的系统和方法将微喷射阵列放置在界定流体流动的表面上。 然后主动操纵这些微喷射阵列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。

    VORTEX GENERATION DEVICE
    2.
    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

    Applicant: Brian R. Smith ,  Patrick J. Yagle

    Inventor： Brian R. Smith ,  Patrick J. Yagle

    IPC: B64C1/38

    CPC classification number: B64C23/06 ,  Y02T50/162

    Abstract: 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.

    Abstract translation: 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。

    System and method to control flowfield vortices with micro-jet arrays
    3.
    发明授权
    System and method to control flowfield vortices with micro-jet arrays 有权
    用微喷射阵列控制流场涡旋的系统和方法

    公开(公告)号：US07510149B2

    公开(公告)日：2009-03-31

    申请号：US10909615

    申请日：2004-08-02

    Applicant: Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    Inventor： Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    IPC: B64C21/04

    CPC classification number: B64C21/02 ,  B64C2230/18 ,  Y02T50/166

    Abstract: The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices within the fluid flow places micro-jet arrays on surfaces bounding the fluid flow. These micro-jet arrays are then 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.

    Abstract translation: 本发明提供一种用于使用微喷射阵列主动地操纵和控制在表面上的流体流动内的空气动力学或流体动力学流场涡旋的系统和方法。 用于主动操纵和控制流体流动内的流场旋涡的起始点，大小和轨迹的系统和方法将微喷射阵列放置在界定流体流动的表面上。 然后主动操纵这些微喷射阵列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。

    MICROVANES FOR AIRCRAFT AFT BODY DRAG REDUCTION
    4.
    发明申请
    MICROVANES FOR AIRCRAFT AFT BODY DRAG REDUCTION 有权
    飞机机身减速机的微型飞机

    公开(公告)号：US20110180146A1

    公开(公告)日：2011-07-28

    申请号：US12406819

    申请日：2009-03-18

    Applicant: Brian R. Smith ,  Brant H. Maines ,  Edward C. Ma ,  Edward A. DiGirolamo ,  Patrick J. Yagle

    Inventor： Brian R. Smith ,  Brant H. Maines ,  Edward C. Ma ,  Edward A. DiGirolamo ,  Patrick J. Yagle

    IPC: B64C1/38

    CPC classification number: B64C23/06 ,  B64C1/0009 ,  B64C2230/26 ,  F15D1/0035 ,  Y02T50/12 ,  Y02T50/162 ,  Y02T50/166 ,  Y10T137/0318

    Abstract: The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.

    Abstract translation: 本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。 该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。 在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度， 减阻元件被定位。

    Method and system of pulsed or unsteady ejector
    5.
    发明授权
    Method and system of pulsed or unsteady ejector 失效
    脉冲或不稳定喷射器的方法和系统

    公开(公告)号：US06308740B1

    公开(公告)日：2001-10-30

    申请号：US09639187

    申请日：2000-08-15

    Applicant: Brian R. Smith ,  Daniel N. Miller ,  Patrick J. Yagle ,  Erich E. Bender ,  Kerry B. Ginn

    Inventor： Brian R. Smith ,  Daniel N. Miller ,  Patrick J. Yagle ,  Erich E. Bender ,  Kerry B. Ginn

    IPC: E03B500

    CPC classification number: F02C9/50 ,  F02C7/04 ,  F04B45/04 ,  F04F5/16 ,  F04F5/54 ,  Y10T137/87619 ,  Y10T137/87652

    Abstract: The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situated within a secondary flow field. This secondary fluid flow is bounded within the walls of an ejector or shroud. The secondary and primary fluid flows meet within the ejector shroud section wherein the secondary fluid flow is entrained by the primary fluid flow. The geometry of the ejector shroud section where the primary and secondary fluids mix is such as to allow the beginning of primary injector pulse to be synchronized with an acoustic wave moving upstream through the ejector initiated by the exiting of the previous pulse from the ejector shroud. The ejector's geometric properties are determined by the acoustic properties, frequency, duty cycle, and amplitude, of the pulsed primary fluid flow. Furthermore, the frequency, duty cycle and amplitude of the primary fluid flow may be varied in order to vary the efficiency of the injector.

    Abstract translation: 本发明揭示了一种用于在用于从次级源泵送较低速度流体的流体喷射器中更有效地喷射主流体流的方法和装置。 在一个实施例中，主流体流是包含在位于二次流场内的内部喷嘴内的脉冲或不稳定流体流。 该次级流体流动在喷射器或护罩的壁内。 次级和初级流体流动在喷射器护罩部分内相交，其中次流体流被主流体流动夹带。 初级和次级流体混合的喷射器护罩部分的几何形状允许初级喷射器脉冲的开始与通过喷射器的上游移动的声波同步，该喷射器由从喷射器护罩的先前脉冲的离开开始。 喷射器的几何特性由脉冲初级流体流的声学特性，频率，占空比和幅度决定。 此外，可以改变初级流体流的频率，占空比和幅度，以改变喷射器的效率。

    Vortex generation device
    6.
    发明授权
    Vortex generation device 有权
    涡流生成装置

    公开(公告)号：US09079658B2

    公开(公告)日：2015-07-14

    申请号：US12869884

    申请日：2010-08-27

    Applicant: Brian R. Smith ,  Patrick J. Yagle

    Inventor： Brian R. Smith ,  Patrick J. Yagle

    IPC: B64C1/38 ,  B64C23/06

    CPC classification number: B64C23/06 ,  Y02T50/162

    Abstract: 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.

    Abstract translation: 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。

    System and method to control flowfield vortices with micro-jet arrays
    7.
    发明授权
    System and method to control flowfield vortices with micro-jet arrays 有权
    用微喷射阵列控制流场涡旋的系统和方法

    公开(公告)号：US08038102B2

    公开(公告)日：2011-10-18

    申请号：US12319585

    申请日：2009-01-09

    Applicant: Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    Inventor： Daniel N. Miller ,  Philip P. Truax ,  Patrick J. Yagle

    IPC: B64C21/04

    CPC classification number: B64C21/02 ,  B64C2230/18 ,  Y02T50/166

    Abstract: The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices within the fluid flow places micro-jet arrays on surfaces bounding the fluid flow. These micro-jet arrays are then 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.

    Abstract translation: 本发明提供一种用于使用微喷射阵列主动地操纵和控制在表面上的流体流动内的空气动力学或流体动力学流场涡旋的系统和方法。 用于主动操纵和控制流体流动内的流场旋涡的起始点，大小和轨迹的系统和方法将微喷射阵列放置在界定流体流动的表面上。 然后主动操纵这些微喷射阵列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。

    Microvanes for aircraft aft body drag reduction
    9.
    发明授权
    Microvanes for aircraft aft body drag reduction 有权
    飞机尾灯微型车身减阻

    公开(公告)号：US08226038B2

    公开(公告)日：2012-07-24

    申请号：US12406819

    申请日：2009-03-18

    Applicant: Brian R. Smith ,  Brant H. Maines ,  Edward C. Ma ,  Edward A. DiGirolamo ,  Patrick J. Yagle

    Inventor： Brian R. Smith ,  Brant H. Maines ,  Edward C. Ma ,  Edward A. DiGirolamo ,  Patrick J. Yagle

    IPC: B64C1/38

    CPC classification number: B64C23/06 ,  B64C1/0009 ,  B64C2230/26 ,  F15D1/0035 ,  Y02T50/12 ,  Y02T50/162 ,  Y02T50/166 ,  Y10T137/0318

    Abstract: The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.

    Abstract translation: 本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。 该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。 在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度， 减阻元件被定位。

    Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle
    10.
    发明授权
    Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle 有权
    不对称注入到高纵横比/复数几何喷嘴的亚音速流中的方法和装置

    公开(公告)号：US06962044B1

    公开(公告)日：2005-11-08

    申请号：US09621795

    申请日：2000-07-21

    Applicant: Daniel N. Miller ,  Patrick J. Yagle ,  Kerry B. Ginn ,  Jeffrey W. Hamstra

    Inventor： Daniel N. Miller ,  Patrick J. Yagle ,  Kerry B. Ginn ,  Jeffrey W. Hamstra

    IPC: F02K1/28 ,  F02K1/30

    CPC classification number: F02K1/30 ,  F02K1/28

    Abstract: The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric injection into the subsonic portion of the fluid flow. The present invention vectors the primary flow by partially blocking the flow with an opposed flow across the flow field. A fluidic flow field is defined in a flow container that directs a pressurized, primary fluidic flow from the container towards an exit of the container. A nozzle may cooperate with the exit of the flow container to control the fluidic flow as it exits the flow container. One or more injectors associated with the container are proximate to the effect throat of the primary flow while other are located downstream of to introduce an opposing fluidic flow that interacts with the primary fluidic flow. A controller associated with the injectors directs the injectors to provide the opposing flow as needed to achieve a desired partial blockage of the primary flow, thereby vectoring the primary flow.

    Abstract translation: 本发明揭示了一种用于控制流体流动的有效面积和推力矢量角的方法和装置。 在一个实施例中，使用对流体流的亚音速部分的不对称注入，将流体流控制在先进的高纵横比的复合孔径几何喷嘴中。 本发明通过跨过流场的相对流部分地阻断流动来对主流进行矢量化。 在流动容器中限定流体流场，其将来自容器的加压的初级流体流引导到容器的出口。 喷嘴可以与流动容器的出口配合，以在流体流动离开流动容器时控制流体流动。 与容器相关联的一个或多个注射器靠近主流的效应，而另一个位于下游，以引入与主流体流相互作用的相反的流体流。 与注射器相关联的控制器引导喷射器以根据需要提供相对的流动，以实现初级流的期望的部分阻塞，从而对主流进行矢量化。

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