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    Apparatus for reducing drag of a transverse duct exit flow
    2.
    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.

    Recessed lift spoiler assembly for airfoils
    4.
    发明授权
    Recessed lift spoiler assembly for airfoils 有权

    公开(公告)号：US09845147B2

    公开(公告)日：2017-12-19

    申请号：US14262647

    申请日：2014-04-25

    申请人： Northrop Grumman Systems Corporation

    发明人： Mark F. Emerick

    IPC分类号： B64C21/02 ,  B64C39/10

    CPC分类号： B64C21/02 ,  B64C39/10 ,  B64C2039/105 ,  B64C2230/06 ,  Y02T50/166

    摘要： A spoiler assembly is provided that is engageable to a UAV that defines a body, an outer surface and an inner surface. The spoiler assembly comprises a spoiler, translatably connected to the UAV inner surface adjacent a first portion of the spoiler aperture. The spoiler defines an upper surface and an outer surface, the upper surface being substantially the same size and shape as the spoiler aperture. A spoiler shroud is connected to the UAV inner surface and extends within the UAV body about at least a portion of the spoiler aperture. A spoiler activating mechanism is secured to the UAV inner surface and connected the spoiler lower surface. The mechanism is operative to translate the spoiler between a first position wherein the spoiler upper surface is substantially flush with the UAV outer surface, and second a position, wherein the spoiler upper surface is disposed substantially within the UAV body.

    RADAR ENERGY ABSORBING DEFORMABLE LOW DRAG VORTEX GENERATOR
    5.
    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.

    Drag reduction utilizing driven micro-cavities
    6.
    发明授权
    Drag reduction utilizing driven micro-cavities 有权
    使用驱动微腔减阻

    公开(公告)号：US09308987B1

    公开(公告)日：2016-04-12

    申请号：US14451247

    申请日：2014-08-04

    申请人： The Curators of the University of Missouri

    发明人： David W. Riggins

    IPC分类号： B64C1/38 ,  B64C21/02

    CPC分类号： B64C21/02 ,  B64C2230/24 ,  Y02T50/166

    摘要： A high-speed vehicle or device presents a surface configured to move through a fluid such that the fluid flows across the surface in a primary flow direction. The vehicle or device also presents a subsurface spaced inwardly from the surface, as well as a plurality of cavity-defining structures that project generally outwardly from the subsurface and extend along the subsurface generally transverse to the primary flow direction. The cavity-defining structures are spaced apart in the primary flow direction. Each adjacent pair of the cavity-defining structures and the subsurface at least in part cooperatively define a cavity therebetween. Fluid rollers or vortices are formed in the cavities, with frictional forces thereby being generated therein in a direction opposite of drag forces on the surface. Each of the cavity-defining structures defines at least one interconnecting channel extending between adjacent ones of the cavities to fluid interconnect said cavities.

    摘要翻译： 高速车辆或设备呈现配置成移动通过流体的表面，使得流体在主流动方向上流过表面。 车辆或装置还具有从表面向内间隔开的地下，以及多个空腔限定结构，其大体上从地下向外突出并且沿着大体横向于主流动方向的地下延伸。 空腔限定结构在主流动方向上间隔开。 每个相邻的空腔限定结构对和至少部分协同地在其间形成腔。 流体辊或涡流形成在空腔中，由此在与表面上的阻力相反的方向上产生摩擦力。 空腔限定结构中的每一个限定了在相邻空腔之间延伸的至少一个互连通道，以使所述空腔流体互连。

    WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT
    9.
    发明申请
    WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT 有权
    飞机，飞机和减少航空拖延和改善最大提升的方法

    公开(公告)号：US20130320150A1

    公开(公告)日：2013-12-05

    申请号：US13851330

    申请日：2013-03-27

    申请人： AIRBUS OPERATIONS GMBH

    发明人： Daniel Reckzeh ,  Burkhard Goelling ,  Matthias Lengers

    IPC分类号： B64C23/06

    CPC分类号： B64C23/069 ,  B64C21/02 ,  Y02T50/164 ,  Y02T50/166

    摘要： A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.

    摘要翻译： 用于飞机的机翼包括从主翼区域的端部延伸到翼尖的前缘和翼尖延伸部。 翼尖延伸部包括至少从主翼区域的端部沿着前缘的翼尖的开口的布置，这些开口连接到用于通过开口输送空气的空气输送装置。 因此，在具有低飞行速度的飞行状态中，围绕翼尖延伸部的流动可以被协调，使得阻力减小并且机翼的升力增加。