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    Apparatus for reducing drag of a transverse duct exit flow
    1.
    发明授权
    Apparatus for reducing drag of a transverse duct exit flow 有权

    公开(公告)号：US11679870B2

    公开(公告)日：2023-06-20

    申请号：US16958606

    申请日：2018-12-13

    申请人： AERO DESIGN LABS LLC

    发明人： Eric A. Ahlstrom ,  Lee Sanders

    IPC分类号： B64C23/06 ,  B64C7/00 ,  B64C21/02

    CPC分类号： B64C23/06 ,  B64C7/00 ,  B64C21/02

    摘要： A fairing assembly is provided about a duct outlet port, which is not parallel to an exterior surface of a vehicle, so as to turn fluid flow exiting the duct outlet port in a direction of surface fluid flow. The fairing assembly includes an upstream vane fairing to orient the surface flow with the angled duct flow, a downstream Coanda fairing to turn transverse duct flow in the direction of the surface flow, and a pair of vortex generators each of which is positioned at an opposing lateral side of the Coanda fairing and angled towards each other to organize the combined fluid flow downstream of the duct outlet port to thereby minimize recirculation. This fairing assembly about the duct outlet port enhances organized mixing of the duct and surface flows, and thereby reduces duct and surface recirculation, duct restriction, and overall vehicle drag.

    RADAR ENERGY ABSORBING DEFORMABLE LOW DRAG VORTEX GENERATOR
    7.
    发明申请
    RADAR ENERGY ABSORBING DEFORMABLE LOW DRAG VORTEX GENERATOR 有权

    公开(公告)号：US20170137115A1

    公开(公告)日：2017-05-18

    申请号：US15227921

    申请日：2016-08-03

    申请人： University of Kansas

    发明人： Ronald M. Barrett

    IPC分类号： B64C23/06 ,  B64C21/00 ,  F15D1/00 ,  H01Q17/00

    CPC分类号： F15D1/004 ,  B64C21/02 ,  B64C23/06 ,  F15D1/003 ,  G03G13/26 ,  G03G13/283 ,  H01Q17/004 ,  H01Q17/008 ,  Y02T50/162

    摘要： A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.) the generation of radar cross-section spikes produced by the VGs themselves.

    HELICOPTER WITH ANTI-TORQUE SYSTEM, RELATED KIT AND METHODS
    8.
    发明申请
    HELICOPTER WITH ANTI-TORQUE SYSTEM, RELATED KIT AND METHODS 审中-公开
    具有抗扭转系统的直升机，相关工具包和方法

    公开(公告)号：US20170001722A1

    公开(公告)日：2017-01-05

    申请号：US15197329

    申请日：2016-06-29

    申请人： BLR AEROSPACE, L.L.C.

    发明人： Michael Carpenter ,  Daniel A. Smith

    IPC分类号： B64C27/82 ,  B64C27/04 ,  B64C27/12 ,  B64C23/06

    CPC分类号： B64C27/82 ,  B64C7/00 ,  B64C23/06 ,  B64C2027/8263 ,  Y02T50/162

    摘要： A strake may extend along a portion of an approaching side of a tail boom of a helicopter. A number of vortex generators (VGs) may extend along a portion of a retreating side of the tail boom. For tail booms with circular cross sections, the strake and the VGs are positioned between approximately 5 and 15 degrees below a horizontal plane of the tail boom when viewed end on, on respective sides of the tail boom. For tail booms with non-circular cross sections, the strake and the VGs is positioned between approximately 5 and 15 degrees above a location where a change in curvature is greatest (e.g., where flow separation would otherwise occur) on a bottom half of the tail boom when viewed end on, on respective sides of the tail boom. A fairing may be located on the retreating side on the upper half of the tail boom, to create an asymmetric profile.

    摘要翻译： 一个行星架可以沿直升机尾巴的接近侧的一部分延伸。 许多涡流发生器（VG）可以沿尾臂的后退侧的一部分延伸。 对于具有圆形横截面的尾部悬臂，当尾端在尾部吊臂的相应侧上观察时，挡板和VG位于尾吊杆的水平面下方约5度至15度之间。 对于具有非圆形横截面的尾部悬臂，排挡和VG位于距离最小的位置（例如，否则将发生流动分离的地方）之间的大约5至15度之间 观察结束时的吊臂在尾部吊杆的相应侧面。 整流罩可以位于尾臂上半部的后退侧，以形成不对称的轮廓。

    SWEPT GRADIENT BOUNDARY LAYER DIVERTER
    9.
    发明申请
    SWEPT GRADIENT BOUNDARY LAYER DIVERTER 有权
    SWEPT梯度边界层流

    公开(公告)号：US20160376018A1

    公开(公告)日：2016-12-29

    申请号：US14750718

    申请日：2015-06-25

    申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION

    发明人： TRAJAEN J. TROIA ,  JOHN F. MANGUS

    IPC分类号： B64D33/02 ,  B64D47/08 ,  B64C23/04

    CPC分类号： B64D33/02 ,  B64C21/10 ,  B64C23/04 ,  B64C23/06 ,  B64D47/08 ,  B64D2033/0226 ,  B64D2033/026 ,  Y02T50/162 ,  Y02T50/166

    摘要： A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.

    摘要翻译： 用于飞机的扫掠梯度空气边界层分流器。 飞行器包括机身和用于飞行器发动机的进气口，其中空气入口包括在入口前缘的整流罩。 分流器包括形成在机身中的V形斜坡部分，该平面部分靠近整流罩的前部和前部，其中斜面部分向下延伸离开机身的外表面朝向飞行器的内部。 分流器还包括形成在机身中的V形槽部分，并且定位成与斜坡部分和空气入口之间的斜坡部分相邻并且与之形成一体。 流过机身的空气朝向整流罩扩张并被斜坡部分和槽部分压缩，以便产生产生涡流的压力梯度，以使边界层气流绕空气入口重新定向。