公开(公告)号：US11679870B2

公开(公告)日：2023-06-20

申请号：US16958606

申请日：2018-12-13

Applicant: AERO DESIGN LABS LLC

Inventor： Eric A. Ahlstrom ,  Lee Sanders

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

CPC classification number: B64C23/06 ,  B64C7/00 ,  B64C21/02

Abstract: 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.

公开(公告)号：US20180265183A1

公开(公告)日：2018-09-20

申请号：US15986477

申请日：2018-05-22

Applicant: President and Fellows of Harvard College ,  University of South Carolina

Inventor： Katia Bertoldi ,  August G. Domel ,  George V. Lauder ,  Mehdi Saadat ,  Hossein Haj-Hariri

IPC: B64C23/06

CPC classification number: B64C23/06 ,  B64C2230/20 ,  B64C2230/26 ,  Y02T50/162 ,  Y02T50/166 ,  Y02T70/121

Abstract: An aerodynamic device for enhancing lift and reducing drag on a body, comprising a plurality of raised members, each having a symmetric profile and including a central portion having an elongated profile, and first and second outer portions having elongated profiles and arranged substantially parallel to and on opposing sides of the central portion, wherein the plurality of raised members are situated adjacent one another to form a continuous structure on or defining at least a portion of a surface of the body and oriented such that the raised members are substantially aligned with a direction of localized flow on the body. An aerodynamic device for enhancing lift and reducing drag of a flying disc, wherein the plurality of raised members are situated adjacent one another to form a continuous structure and the raised members are oriented in a substantially circumferential direction on the surface of the flying disc.

公开(公告)号：US10071799B2

公开(公告)日：2018-09-11

申请号：US15265920

申请日：2016-09-15

Applicant: Airbus Defence and Space GmbH

Inventor： Karin Bauer ,  Markus Blechschmidt ,  Wolfgang Nitsche

IPC: B64C23/00 ,  B64C23/06 ,  B64G1/22 ,  G05B19/042 ,  B64C21/08

CPC classification number: B64C23/005 ,  B64C21/08 ,  B64C23/06 ,  B64C2230/02 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  B64G1/22 ,  G05B19/0428 ,  G05B2219/45207 ,  Y02T50/166

Abstract: A cooperative actuator system for active flow control, a vehicle comprising such cooperative actuator system, and a method for operating an actuator system for active flow control. The cooperative actuator system includes actuators, a control unit, and a data unit. The actuators are distributed along the surface in at least a first group and a second group downstream of the first group. The control unit is configured to control the actuators of the first group so that they form a first flow structure along the surface. The data unit is configured to provide data of the first flow structure. The control unit is further configured to control the actuators of the second group based on the data of the first flow structure, so that the actuators of the second group cooperatively interact with the first flow structure to form a second flow structure along the surface.

公开(公告)号：US20180194456A1

公开(公告)日：2018-07-12

申请号：US15404810

申请日：2017-01-12

Applicant: The Boeing Company

Inventor： Gene Arthur Quandt ,  Matthew James Hemsath ,  Tracy L. Duvall ,  David Brian Christman ,  Frederick T. Calkins

IPC: B64C21/00 ,  B64C9/14 ,  B64C23/00

CPC classification number: B64C3/36 ,  B64C9/18 ,  B64C23/06 ,  B64D27/18

Abstract: A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft.

公开(公告)号：US20170305528A1

公开(公告)日：2017-10-26

申请号：US15587902

申请日：2017-05-05

Applicant: AIRBUS OPERATIONS GMBH

Inventor： Rolf EMUNDS

IPC: B64C7/00 ,  B64C9/02 ,  B64C9/16 ,  B64C23/06

CPC classification number: B64C7/00 ,  B64C9/02 ,  B64C9/16 ,  B64C23/06

Abstract: An aircraft comprising a casing for a lifting aid, the casing comprising at least one strake which extends essentially in a protruding manner in the direction of flight in relation to an outer surface of the casing.

公开(公告)号：US20170175531A1

公开(公告)日：2017-06-22

申请号：US14975291

申请日：2015-12-18

Applicant: Amazon Technologies, Inc.

Inventor： Brian C. Beckman ,  Gur Kimchi ,  Allan Ko

IPC: F01D5/14 ,  B64C27/58 ,  B64C11/20

CPC classification number: F01D5/141 ,  B64C23/06 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2230/14 ,  B64C2230/26 ,  B64C2230/28 ,  Y02T50/162 ,  Y02T50/166 ,  Y02T50/66

Abstract: Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.

公开(公告)号：US20170137115A1

公开(公告)日：2017-05-18

申请号：US15227921

申请日：2016-08-03

Applicant: University of Kansas

Inventor： Ronald M. Barrett

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

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

Abstract: 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.

公开(公告)号：US20170001722A1

公开(公告)日：2017-01-05

申请号：US15197329

申请日：2016-06-29

Applicant: BLR AEROSPACE, L.L.C.

Inventor： Michael Carpenter ,  Daniel A. Smith

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

CPC classification number: B64C27/82 ,  B64C7/00 ,  B64C23/06 ,  B64C2027/8263 ,  Y02T50/162

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20160376018A1

公开(公告)日：2016-12-29

申请号：US14750718

申请日：2015-06-25

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： TRAJAEN J. TROIA ,  JOHN F. MANGUS

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

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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20160298646A1

公开(公告)日：2016-10-13

申请号：US14681441

申请日：2015-04-08

Applicant: General Electric Company

Inventor： Moorthi Subramaniyan ,  Manjunath Bangalore Chengappa ,  Pradeep Patel

IPC: F04D29/54 ,  F01D25/28 ,  F01D9/04 ,  B23P19/00

CPC classification number: F04D29/542 ,  B23P19/00 ,  B64C23/06 ,  F01D5/145 ,  F01D9/045 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F01D25/30 ,  F04D29/544 ,  F04D29/681 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/127

Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.

Abstract translation: 提供了一种用于燃气轮机动力系统的燃气轮机扩散器。 扩散器包括环形内壁和围绕内壁的环形外壁，使得在内壁和外壁之间限定气体路径。 扩散器还包括跨越气体路径从内壁延伸到外壁的多个周向间隔的支柱。 支柱中至少有一个具有襟翼。