公开(公告)号：US20160023748A1

公开(公告)日：2016-01-28

申请号：US14341184

申请日：2014-07-25

申请人： Scott R. Kempshall

发明人： Scott R. Kempshall

IPC分类号： B64C3/44 ,  B64B1/58 ,  B64C3/54 ,  B64B1/08 ,  B64B1/14

CPC分类号： B64C3/46 ,  B64B1/08 ,  B64B1/14 ,  B64B1/26 ,  B64B1/58 ,  B64B2201/00 ,  B64C3/48 ,  B64C3/54 ,  B64C3/546 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/105 ,  F03D1/04 ,  F03D9/25 ,  F03D9/32 ,  F05B2240/921 ,  Y02E10/725

摘要： The present invention is a variable geometry lighter-than-air (LTA) aircraft that is adapted to morph its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

摘要翻译： 本发明是一种可变几何型轻型空中（LTA）飞机，其适于将其形状从对称横截面浮力工艺变形到非对称提升体，甚至变形成对称零升力构造。 基本结构是具有可移动隆起的半刚性飞艇。 仰角的运动调节上表面和/或下表面的弯度，以实现提升体的变化形状。 这种转变改变了飞行器的升力和阻力特性，以改变飞行特性。 转换可以在飞行器机载时完成，并且不需要任何地面支撑设备。

公开(公告)号：US08870125B2

公开(公告)日：2014-10-28

申请号：US13187634

申请日：2011-07-21

申请人： Michael A. Balzer ,  Gregory M. Santini ,  Michael K. Klein

发明人： Michael A. Balzer ,  Gregory M. Santini ,  Michael K. Klein

IPC分类号： B64C3/50 ,  B64C9/16

CPC分类号： B64C9/16 ,  B64C3/46 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/44

摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

摘要翻译： 一种用于气动地致动分开的翼片的系统，其铰接地安装在翼型件的后缘附近或其后缘。 该系统包括设置在分裂翼片和翼型件的上表面之间的气囊系统。 襟翼是一个小和弦（通常是总翼弦的1-3％）长跨度下面板，通过铰链或柔性下皮肤与翼型后缘分离。 通过可充气膀胱系统气动地驱动分裂瓣的部署。 分裂瓣可以存在于固定的翼缘后缘，移动的翼片后缘或尾翼的后缘。 气动气囊提供分布的力以延伸和缩回分裂瓣。 这种气动方式消除了额外的阻力，降低了成本和重量，并减轻了颤抖的担忧。

公开(公告)号：US20050029406A1

公开(公告)日：2005-02-10

申请号：US10866103

申请日：2004-06-14

申请人： Kay Dittrich

发明人： Kay Dittrich

IPC分类号： B64C3/46 ,  B64C13/40 ,  B64C13/04

CPC分类号： B64C3/46 ,  B64C13/40

摘要： A cellular actuator device suitable for a control surface of an aircraft or space craft has a number of elementary cells which are combined to a common arrangement and are formed by pressure-tight chambers. The elementary cells can be acted upon by a pressure medium and, when acted upon by the pressure medium, can be deformed in at least one work direction while changing their length. The elementary cells are coupled for combining their length changes in the at least one working direction to an overall movement of the elementary cell arrangement. The actuator device is particularly suitable for actuating a control surface of an aircraft or spacecraft.

摘要翻译： 适用于飞机或航天飞机的控制表面的蜂窝致动器装置具有多个基本单元，它们组合成共同的布置，并由压力密封室形成。 基本细胞可以被压力介质作用，并且当被压力介质作用时，可以在改变其长度的同时在至少一个工作方向上变形。 耦合基本单元以将它们在至少一个工作方向上的长度变化与基本单元布置的整体运动相结合。 致动器装置特别适于致动飞行器或航天器的控制表面。

公开(公告)号：US06443394B1

公开(公告)日：2002-09-03

申请号：US09666996

申请日：2000-09-21

申请人： Norbert A. Weisend, Jr.

发明人： Norbert A. Weisend, Jr.

IPC分类号： B64D1500

CPC分类号： B64D15/166 ,  B64C3/46 ,  Y02T50/14

摘要： An airfoil device (10) for attachment to the wing (14) of an aircraft (12). The airfoil device (10) has a chamber (30) which is inflatable to provide a lift-enhancing airfoil geometry to the wing (14) and other chambers (32) which are inflatable to provide deicing forces to remove ice accumulation on the wing (14). When installed on the wing (14), the airfoil device (10) closely conforms to the wing's airfoil geometry (e.g., low camber, sharp leading edge) when the lift-enhancing chamber (30) and the deicing chambers (32) are in a deflated condition. The lift-enhancing chamber (30) can be inflated during take-off and landing to provide a high camber and less sharp airfoil geometry. If ice accumulates on the wing (14) during high speed flight, the deicing chambers (32) can be repeatedly inflated/deflated for ice removal purposes.

摘要翻译： 一种用于附接到飞机（12）的机翼（14）的翼型装置（10）。 翼型装置（10）具有可充气的室（30），以向机翼（14）和其他室（32）提供提升增强型翼面几何形状，其可充气以提供除冰力以移除机翼上的积冰 14）。 当安装在机翼（14）上时，当提升增强室（30）和除冰室（32）处于...中时，翼型装置10紧密地与翼的翼面几何形状（例如，低外倾角，尖锐的前缘） 一个放气的状况。 提升增强室（30）在起飞和着陆期间可以被充气以提供高的弯度和较不锋利的机翼几何形状。 如果在高速飞行期间冰积聚在机翼（14）上，则除冰室（32）可以反复充气/放气以进行除冰目的。

公开(公告)号：US06358021B1

公开(公告)日：2002-03-19

申请号：US09706051

申请日：2000-11-03

申请人： Cleopatra Cabuz

发明人： Cleopatra Cabuz

IPC分类号： F04B1700

CPC分类号： H02N1/006 ,  B64C3/38 ,  B64C3/46 ,  B64C13/48 ,  B64C13/50 ,  B64C21/10 ,  B64C23/005 ,  B81B3/0054 ,  B81B2203/053 ,  F04B43/043 ,  F15B15/103 ,  F15C5/00 ,  F15D1/12 ,  F16K99/0001 ,  F16K99/0015 ,  F16K99/0028 ,  F16K99/0051 ,  F16K2099/0078 ,  Y02T50/166

摘要： An actuator device controlling the shape of a flexible surface having a quasi-continuum in a plurality of locations. The device includes a plurality of individual cells arranged in an array for contact with the flexible surface. The cells comprise a cell body having an upper film portion and a lower film portion and an open central portion. The upper film portion is in contact with the flexible surface. A post is mounted in the open central portion and fixedly attached to the upper film portion and the lower film portion, the post defining a vertical axis of movement. The upper and lower film portions have electrodes mounted thereon respectively, positioned on the face of the upper and lower film portions and facing each other. A central diaphragm has electrodes on its outer surfaces and an open central portion surrounding the post A power supply operably connected to the electrodes for causing selective cooperative electrostatic activation between them to move the post along the vertical axis to cause the upper film portion to move that portion of the flexible surface in which the upper film portion is in contact. In a preferred embodiment, the cell body has a circular cross section so that the post moves vertically upward and downward to raise or lower the portion of the flexible surface in contact with the upper film portion upon application of electrostatic potential between the electrodes.

摘要翻译： 控制在多个位置具有准连续体的柔性表面的形状的致动器装置。 该装置包括布置成阵列中的与柔性表面接触的多个单独电池。 电池包括具有上膜部分和下膜部分以及开放中心部分的电池体。 上部薄膜部分与柔性表面接触。 柱安装在打开的中心部分中并且固定地附接到上膜部分和下膜部分，柱体限定了垂直运动轴线。 上下胶片部具有分别安装在上胶卷部分和下胶片部分的表面上彼此面对的电极。 中心隔膜在其外表面上具有电极，并且打开的中心部分围绕可操作地连接到电极的柱A电源，用于在它们之间引起选择性协同的静电激活，以沿垂直轴线移动柱，以使上膜部分移动 柔性表面的上部膜部分接触的部分。 在优选实施例中，电池体具有圆形横截面，使得柱在垂直上下移动以在施加电极之间的静电电位时上升或下降与上部膜部分接触的柔性表面的部分。

公开(公告)号：US2934288A

公开(公告)日：1960-04-26

申请号：US47539854

申请日：1954-12-15

申请人： BENDIX AVIAT CORP

发明人： HALE MACINTYRE CHARLES

IPC分类号： B64C3/46 ,  F02C7/042

CPC分类号： B64C3/46 ,  F02C7/042

公开(公告)号：US2306759A

公开(公告)日：1942-12-29

申请号：US34690340

申请日：1940-07-23

申请人： GOODRICH CO B F

发明人： SEARS CLIFFORD T

IPC分类号： B64C3/46 ,  B64C21/02

CPC分类号： B64C3/46 ,  B64C21/02 ,  B64C2230/06 ,  B64C2230/20 ,  Y02T50/166

公开(公告)号：US20180171975A1

公开(公告)日：2018-06-21

申请号：US15545830

申请日：2016-01-24

申请人： Dieter Röhm

发明人： Dieter Röhm

IPC分类号： F03D7/02 ,  B64C9/02 ,  B64C3/46 ,  B64C9/18 ,  B64C9/20 ,  F03B3/12 ,  F03D1/06 ,  F03D80/30 ,  F15D1/10

CPC分类号： F03D7/0232 ,  B64C3/46 ,  B64C9/00 ,  B64C9/02 ,  B64C9/18 ,  B64C9/20 ,  B64C23/00 ,  F03B3/123 ,  F03D1/0633 ,  F03D1/0675 ,  F03D7/0252 ,  F03D80/30 ,  F05B2210/16 ,  F05B2240/31 ,  F05B2240/311 ,  F05B2240/98 ,  F05B2250/183 ,  F05B2260/507 ,  F05B2260/901 ,  F05B2260/964 ,  F05B2270/402 ,  F05B2270/404 ,  F15D1/10 ,  Y02E10/223 ,  Y02E10/721 ,  Y02E10/723 ,  Y02T50/32

摘要： The invention relates to a device of a safety system and/or resource and energy-efficiency improvement system for influencing the flow around an aero- or hydrodynamic body, preferably an aerofoil, according to the principle of a back-flow flap, characterized in that: said device, together with the aero- or hydrodynamic body, in particular aerofoil, form at least a partial shift of the delimitation of the flap region by means of the back-flow flap and the delimiting component thereof when the back-flow flap is partially and/or completely raised, thus influencing the trailing edge separation vortex/vortices and/or the flap separation vortex/vortices; and in that the delimitation of the flap region shifts completely up to or beyond the profile trailing edge, or shifts only to a section in front of the profile trailing edge. The delimitation component is movably connected to the aerofoil by means of a basic element and is preferably permanently secured and/or releasably secured for maintenance purposes, thus ensuring a long service life for the rotor blade and/or wind turbine and/or flap system, preferably >5 years, particularly preferably >10 years, and most particularly preferably >=20 years, and/or thus optionally allowing simple removal/replacement.

公开(公告)号：US20050056731A1

公开(公告)日：2005-03-17

申请号：US10357022

申请日：2003-02-03

申请人： Brian Hamilton ,  Stephen Guymon ,  Gregory Dockter ,  Ahmed Hassan

发明人： Brian Hamilton ,  Stephen Guymon ,  Gregory Dockter ,  Ahmed Hassan

IPC分类号： B64C3/30 ,  B64C3/38 ,  B64C3/46 ,  B64C3/54 ,  B64C5/10 ,  B64C27/473 ,  B64C3/44

CPC分类号： B64C3/54 ,  B64C3/30 ,  B64C3/38 ,  B64C3/46 ,  B64C5/10 ,  B64C27/473 ,  B64C2003/445 ,  Y02T50/14

摘要： An airfoil member (14) includes a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. The exterior wall (32) includes a layer with one or more fibers embedded therein. The exterior wall (32) controls size, shape, and expansion ability of the geometric morphing device (18).

摘要翻译： 机翼构件（14）包括几何变形装置（18）。 几何变形装置（18）具有可充气构件（30）。 可膨胀构件（30）具有外壁（32）和多个充气状态。 外壁（32）包括具有嵌入其中的一个或多个纤维的层。 外壁（32）控制几何变形装置（18）的尺寸，形状和膨胀能力。

公开(公告)号：US06786457B2

公开(公告)日：2004-09-07

申请号：US10268558

申请日：2002-10-10

申请人： Gregory E. Dockter ,  Brian K. Hamilton

发明人： Gregory E. Dockter ,  Brian K. Hamilton

IPC分类号： B64C346

CPC分类号： B64C3/46 ,  B64C3/38 ,  B64C3/54 ,  Y02T50/14

摘要： An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. Multiple layers are coupled to at least a portion of the exterior wall (32) and control size, shape, and expansion ability of the geometric morphing device (18). The geometric morphing device (18) is adjustable in size and shape by changing inflated state of the inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

摘要翻译： 提供了包括几何变形装置（18）的翼型件（14）。 几何变形装置（18）具有可充气构件（30）。 可膨胀构件（30）具有外壁（32）和多个充气状态。 多层联接到外壁（32）的至少一部分并且控制几何变形装置（18）的尺寸，形状和膨胀能力。 几何变形装置（18）通过改变可膨胀构件（30）的膨胀状态来调整尺寸和形状。 还提供了翼型构件改变系统（12）及其执行方法以及形成几何变形装置（18）的方法。