公开(公告)号：WO2014006422A2

公开(公告)日：2014-01-09

申请号：PCT/GB2013051792

申请日：2013-07-05

Applicant: HARKIN PAUL

Inventor： HARKIN PAUL

IPC: E04B1/19

CPC classification number: E04B1/1903 ,  A47C3/00 ,  B60N2/68 ,  B64C1/06 ,  B64C1/22 ,  B64C3/40 ,  B64C3/48 ,  B64C2001/0045 ,  B64D11/0638 ,  B64D11/06395 ,  B64D11/064 ,  E01D6/00 ,  E01D19/00 ,  E04B1/19 ,  E04B2001/1924 ,  E04B2001/1927 ,  E04B2001/1942 ,  E04B2001/1987 ,  E04B2001/199 ,  Y10T403/32451

Abstract: An adjustable structure (1) comprising a first structural layer (10) defined by a first array of extendable and/or retractable rods or beams (11, 11a, 11b) pivotally connected to each other at their ends and a second structural layer (20) connected to the first structural layer (10) and defined by a second array of extendable and/or retractable rods or beams (21, 21a, 21b) pivotally connected to each other at their ends, wherein at least a portion of the second layer (20) is outside the volume defined by the first structural layer (10) and the extendable and/or retractable rods or beams in the second arrayare more densely packed than the extendable and/or retractable rods or beams in the first array.

Abstract translation: 一种可调节结构（1），包括由第一组可延伸和/或可伸缩的杆或梁（11,11a，11b）的第一阵列限定的第一结构层（10），所述第一组可延伸的杆或梁在其端部彼此枢转地连接， ）连接到第一结构层（10）并且由在其端部彼此枢转地连接的第二可延伸杆和/或可伸缩杆或梁（21,21a，21b）阵列限定，其中第二层 （20）位于由第一结构层（10）限定的体积之外并且第二阵列中的可伸缩杆或梁比第一阵列中的可伸缩杆或梁更密集地堆叠。

公开(公告)号：WO2010101699A3

公开(公告)日：2010-10-28

申请号：PCT/US2010023503

申请日：2010-02-08

Applicant: BOEING CO ,  GRIP ROBERT E

Inventor： GRIP ROBERT E

IPC: B64C3/48

CPC classification number: B64C3/48 ,  B64C9/16

Abstract: An apparatus comprises a structure (303) having a first side (302), a second side (304) substantially opposite to the first side, a flexible skin (318), and a plurality of deformable assemblies. The flexible skin is attached to the first side and the second side of the structure. The plurality of deformable assemblies is moveably connected to the structure, in which each deformable assembly in the plurality of deformable assemblies has a vertex and a base. The each deformable assembly in the plurality of deformable assemblies has a height that is capable of changing to change a shape of the structure and a shape of the flexible skin.

Abstract translation: 一种装置包括具有第一侧（302），与第一侧基本相对的第二侧（304），柔性表皮（318）和多个可变形组件的结构（303）。 柔性皮肤附接到结构的第一侧和第二侧。 多个可变形组件可移动地连接到结构，其中多个可变形组件中的每个可变形组件具有顶点和底座。 多个可变形组件中的每个可变形组件具有能够改变以改变结构的形状和柔性皮肤的形状的高度。

公开(公告)号：WO2009137143A1

公开(公告)日：2009-11-12

申请号：PCT/US2009/034628

申请日：2009-02-20

Applicant: CORNERSTONE RESEARCH GROUP, INC. ,  HEMMELGARN, Chirstopher, Douglas ,  CABLE, Kristin, Marie ,  KIRBY, Brandon, Charles ,  PELLEY, Bryan, Michael

Inventor： HEMMELGARN, Chirstopher, Douglas ,  CABLE, Kristin, Marie ,  KIRBY, Brandon, Charles ,  PELLEY, Bryan, Michael

IPC: B64C21/10

CPC classification number: B64C3/48 ,  B64C2003/445 ,  F03D1/0675 ,  F05B2240/311 ,  Y02E10/721 ,  Y02T50/14

Abstract: Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic load exerted on the body by the flow is one such parameter, typically characterized as lift or drag. It is the aim of the present disclosure to teach the use of passive adaptive morphing structures to manage these aerodynamic loads.

Abstract translation: 空气动力学原理的几何变形可以优化其空气动力学性质，增加范围，降低燃料消耗，并改善许多性能参数。 通过流动施加在身体上的空气动力学负载是一个这样的参数，通常被表征为升力或阻力。 本公开的目的是教导使用被动自适应变形结构来管理这些空气动力学负载。

公开(公告)号：WO2007145718A9

公开(公告)日：2008-05-02

申请号：PCT/US2007010438

申请日：2007-04-27

Applicant: FLEXSYS INC ,  HETRICK JOEL A ,  ERVIN GREGORY F ,  KOTA SRIDHAR NMN

Inventor： HETRICK JOEL A ,  ERVIN GREGORY F ,  KOTA SRIDHAR NMN

IPC: B64C3/14

CPC classification number: B64C3/52 ,  B64C3/48 ,  B64C3/50 ,  B64C9/16 ,  B64C9/22 ,  B64C27/473 ,  B64C27/72 ,  Y02T50/34 ,  Y10T74/18056 ,  Y10T74/18288

Abstract: An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with a rib element arranged to overlie the edge of the airfoil. The rib element has first and second rib portions arranged to communicate with respectively associated ones of the upper and lower control surfaces of the airfoil. A first compliant linkage element has first and second ends and is disposed between the first and second rib portions of the rib element, the first and second ends are each coupled to the interior of a respectively associated one of the first and second rib portions. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of a selectable one of the first and second rib portions in the vicinity of the coupling of the respectively associated end of the first compliant linkage element. The second end is arranged to receive a morphing force, and the rib element is deformed in response to the morphing force. Multiple rib elements can be arranged substantially parallel to one another and configured to morph at respective operating ratios. Additionally, an overlying skin has a thickness that varies over the span.

Abstract translation: 用于具有上和下控制表面的翼型件的边缘变形布置设置有布置成覆盖翼型件的边缘的肋元件。 肋元件具有第一和第二肋部分，所述第一和第二肋部分布置成分别与翼型件的上部和下部控制表面中的相关联的一些连通。 第一柔性连接元件具有第一端和第二端并且设置在肋元件的第一肋部分和第二肋部分之间，第一端部和第二端部分别联接到第一肋部分和第二肋部分中的相应关联的一个的内部。 另外提供了一种驱动连杆，该驱动连杆具有第一和第二驱动连杆端部，第一驱动连杆端部在第一和第二肋部分中的可选的一个的内部连接到第一和第二肋部分的相应关联端部 兼容的连接元件。 第二端布置成接收变形力，并且肋元件响应于变形力而变形。 多个肋元件可以基本彼此平行地布置并且构造成在相应的操作比下变形。 此外，覆盖表层的厚度会随着跨度而变化。

公开(公告)号：WO2005060476A3

公开(公告)日：2005-12-01

申请号：PCT/US2004038364

申请日：2004-11-17

Applicant: GEN MOTORS CORP

Inventor： BROWNE ALAN L ,  JOHNSON NANCY L ,  MC KNIGHT GEOFFREY P ,  MASSEY CAMERON ,  HERRERA GUILLERMO A ,  BARVOSA-CARTER WILLIAM

IPC: B60J1/00 ,  B62D35/00 ,  B62D37/02

CPC classification number: B62D35/00 ,  B62D35/007 ,  B64C3/48 ,  Y02T50/145

Abstract: An airflow control device comprises a body and an active material in operative communication with the body. The active material, such as shape memory material, is operative to change at least one attribute in response to an activation signal. The active material can change its shape, dimensions and/or stiffness producing a change in at least one feature of the airflow control device such as shape, dimension, location, orientation, and/or stiffness to control vehicle airflow to better suit changes in driving conditions such as weather, ground clearance and speed, while reducing maintenance and the level of failure modes. As such, the device reduces vehicle damage due to inadequate ground clearance, while increasing vehicle stability and fuel economy. An activation device, controller and sensors may be employed to further control the change in at least one feature of the airflow control device such as shape, dimension, location, orientation, and/or stiffness of the device. A method for controlling vehicle airflow selectively introduces an activation signal to initiate a change of at least one feature of the device that can be reversed upon discontinuation of the activation signal.

Abstract translation: 气流控制装置包括与主体可操作地连通的主体和活动材料。 诸如形状记忆材料的活性材料可操作以响应于激活信号改变至少一个属性。 活性材料可以改变其形状，尺寸和/或刚度，从而产生气流控制装置的至少一个特征的变化，例如形状，尺寸，位置，取向和/或刚度，以控制车辆气流，以更好地适应驾驶中的变化 条件如天气，离地间隙和速度，同时减少维护和故障模式的水平。 因此，该装置由于不足的离地间隙而减少车辆损坏，同时提高车辆稳定性和燃料经济性。 可以使用激活装置，控制器和传感器来进一步控制气流控制装置的至少一个特征的变化，例如装置的形状，尺寸，位置，取向和/或刚度。 用于控制车辆气流的方法选择性地引入激活信号以启动在停止激活信号时可以反转的装置的至少一个特征的改变。

公开(公告)号：WO2003080432A1

公开(公告)日：2003-10-02

申请号：PCT/US2003/008046

申请日：2003-03-14

Applicant: THE BOEING COMPANY

Inventor： DUNNE, James, P. ,  KILIAN, Kevin, J. ,  PITT, Dale, M. ,  WHITE, Edward, V.

IPC: B64C23/00

CPC classification number: F02C7/042 ,  B64C3/48 ,  B64C23/005 ,  B64D33/02 ,  B64D2033/0226 ,  F05D2300/431 ,  F05D2300/505 ,  Y02T50/672 ,  Y10T16/525

Abstract: The present invention provides an apparatus and method for varyi ng a wall skin to alter airflow over the skin. The apparatus has a first and second end-plates, a plurarity of flexible rods (106) are arranged substantially parallel to substantially define a plane, each flexible rod (106) has a mid-point and first and second ends (107) secured to the first and second end-plates (115) respectively. Mounting structures (112) are slidingly attached to the flexible rods (106) between the mid-point and each end-plate (115), proximate to the end. An elastomer (118) envelops the rods to form a flexible skin. A plurality of shape memory alloy rods (103) are arranged parallel to and define a plane and having each end secured to an end-plate (115), the plurality of shape memory alloy rods (103) being contractible when heated such that upon contraction the plurality of shape memory allow rods (103) will buckle the plurality of flexible rods (106) and the flexible skin (118) to alter airflow over the skin.

Abstract translation: 本发明提供了一种用于改变墙皮以改变皮肤上的气流的装置和方法。 该设备具有第一和第二端板，多个柔性杆（106）基本平行地布置以基本上限定一个平面，每个柔性杆（106）具有中点，第一和第二端（107）固定到 第一和第二端板（115）。 安装结构（112）在靠近端部的中点和每个端板（115）之间滑动地附接到柔性杆（106）。 弹性体（118）包围杆以形成柔韧的皮肤。 多个形状记忆合金棒（103）平行于并限定了一个平面并且每个端部固定到端板（115）上，多个形状记忆合金棒（103）在加热时可收缩，使得在收缩时 多个形状记忆允许杆（103）将扣紧多个柔性杆（106）和柔性皮肤（118）以改变皮肤上的气流。

公开(公告)号：WO2002092428A1

公开(公告)日：2002-11-21

申请号：PCT/NZ2002/000090

申请日：2002-05-09

Applicant: GROVE, Graham, Bond

Inventor： GROVE, Graham, Bond

IPC: B64C21/04

CPC classification number: B64C21/04 ,  B64C3/48 ,  B64C2230/04 ,  B64C2230/16 ,  B64C2230/28 ,  Y02T50/14 ,  Y02T50/166 ,  Y10S416/05

Abstract: Upper surface (13) of an aerofoil (or rotor blade) is provided with nozzles or slots (14, 16) at leading portion (15) and trailing portion (17) to assist attachment of airflow by discharging gas towards trailing edge (11). Gas discharged may be heated, eg coming from rocket-type combustion chambers within the aerofoil. The aerofoil may be adjustable between high profile (as shown) and low profile (for supersonic flight) using jacks that pivot sections of upper surface (13) at leading and trailing edges (10-11).

Abstract translation: 机翼（或转子叶片）的上表面（13）在引导部分（15）和尾部部分（17）处设置有喷嘴或狭槽（14,16），以通过将气体排向后缘（11）来辅助气流附着， 。 排出的气体可能被加热，例如来自机翼内的火箭式燃烧室。 机翼可以使用在前缘和后缘（10-11）上枢转上表面（13）的部分的千斤顶在高廓（如图所示）和低轮廓（用于超音速飞行）之间可调节。

公开(公告)号：WO1998021091A1

公开(公告)日：1998-05-22

申请号：PCT/EP1997006193

申请日：1997-11-07

Applicant: ARRIBI, Philippe

IPC: B64C03/44

CPC classification number: B63H1/26 ,  B63B1/248 ,  B63H1/28 ,  B63H1/36 ,  B64C3/48 ,  F03D1/0608 ,  F05B2210/16 ,  F05B2240/311 ,  Y02E10/721

Abstract: The present invention relates to a flow form to be used in gaseous or liquid moving fluids, comprising a leading edge (4) defining a dividing line for the flowing medium, two opposite lying surfaces (6, 7) along which the medium flows over the flow form, and a downstream end behind which the medium divided by the flow form converges once again. In order to provide a flow form with enhanced energy utilization and/or energy conversion when compared with known flow forms, and which exhibits specially lower flow losses, the invention proposes that the downstream end should consist of an end section (3) which can be elastically folded around a theoretical axis running almost perpendicular to the direction of flow and lying parallel to a surface defined by the leading edge (4) and the direction of flow, wherein the flexibility of the end section (3) is a multiple of that of the main part (2) of the flow form (1) lying in front of the end section (3) in the direction of flow.

Abstract translation: 本发明涉及一种流动体在气态或液态流体介质使用，具有前部，用于限定前缘（4），两个相对的面（6,7）沿其介质流动体周围流动流入的介质中的分割线，并用 下游端，它的后面分流量穿过所述主体介质重新加入。 为了创建一个流动体，其能量利用率和/或功率转换改进了与已知的流体，因此这尤其是还报告更低的流动损失相比，本发明提出，一个端部（3），约假想，大致的下游端 垂直于流动方向和夹紧平行于前缘（4）中的一个和流动面积位于轴线的方向是可弹性弯曲的，其中，所述端部（3）的柔性的，该端部的上游的倍数（3）位于主体部分（2） 是流体（1）。

公开(公告)号：WO1992013758A1

公开(公告)日：1992-08-20

申请号：PCT/US1992000835

申请日：1992-02-03

Applicant: FLEX FOIL TECHNOLOGY, INC.

Inventor： FLEX FOIL TECHNOLOGY, INC. ,  WIDNALL, Sheila, E. ,  WIDNALL, William, S. ,  EVERNHAM, Jeffrey, T. ,  GORGEN, William, E.

IPC: B64C03/52

CPC classification number: B64C3/48 ,  B63B41/00 ,  B63B2039/063 ,  B64C11/30 ,  Y02T50/14

Abstract: A flexible airfoil section for a wing (102) or a blade (258) comprising a streamlined shape and an elastic structure whose stiffness distribution along its chord and span is tailored to provide a desirable cambered shape with proportional increases in camber with increases in lift, mounted to a supporting structure (104) such that the airfoil sections (102) are free to pivot about axes (106, 108) near their leading and trailing edges. In operation, the foil (102) derives much of its lift from elastic bending deformation of its flexible shape, thereby achieving a higher lift than a symmetric foil at the same angle of attack while postponing the onset of flow separation and stall and, for operation in water, of ventilation and cavitation. A wing (102) or blade (258) of general planform comprising flexible elastic airfoil sections which can be used to stabilize, or to control the direction of travel of, as well as provide force for, a watercraft such as a sailboat (236) or a sailboard (224), or for application to a variety of aircraft components (104) and configurations to provide lift and side force and as well can serve as the aerodynamic surfaces of various types of fluid machinery including fans, helicopter rotors and wind turbines operating in subsonic flow.

Abstract translation: 用于翼（102）或叶片（258）的柔性翼型部分包括流线型形状和弹性结构，其弹性结构的刚度分布沿其弦和跨度被调整以提供期望的弧形形状，其随着升力的增加而具有正比的增加， 安装到支撑结构（104），使得所述翼型部分（102）在其前缘和后缘附近绕轴线（106,108）自由枢转。 在操作中，箔（102）从其柔性形状的弹性弯曲变形中导出其大部分电梯，从而在相同的迎角下实现比对称箔更高的升力，同时延迟流动分离和停止的开始，并且为了操作 在水中，通风和空化。 一般平面形状的翼（102）或叶片（258）包括柔性弹性翼型部分，其可用于稳定或控制诸如帆船（236）的船只的行进方向以及为其提供力， 或救生板（224），或用于应用于各种飞行器部件（104）和构造以提供升力和侧向力，并且还可用作各种类型的流体机械的空气动力学表面，包括风扇，直升机转子和风力涡轮机 在亚音速流中操作。

公开(公告)号：WO1984002506A1

公开(公告)日：1984-07-05

申请号：PCT/US1982001797

申请日：1982-12-28

Applicant: THE BOEING COMPANY ,  COLE, James, Byron

Inventor： THE BOEING COMPANY

IPC: B64C03/50

CPC classification number: B64C3/48

Abstract: A variable camber leading edge device having a movable nose section and an upper flexible panel extending rearwardly from the nosesection. To move the nose section between its upper cruise position and a high lift downwardly deflected position, there is attached to the nose section a generally arcuate cam track (46), having its forward and rear portions curving upwardly. The cam track is constrained to move in a generally arcuate path by means of two spaced pair of rollers (48, 50, 52, 54) and it is driven by a pinion gear (55) engaging an upwardly facing middle portion of the track.

Abstract translation: 具有可移动鼻部的可变外倾凸缘装置和从所述鼻部向后延伸的上柔性面板。 为了将鼻部部分在其上巡航位置和高升力向下偏转位置之间移动，鼻部部分附接有大致弓形的凸轮轨道（46），其前部和后部向上弯曲。 凸轮轨道被限制为通过两个间隔开的一对辊（48,50,52,54）在大体上弧形的路径中移动，并且其由与轨道的向上的中间部分接合的小齿轮（55）驱动。