公开(公告)号：US09856013B2

公开(公告)日：2018-01-02

申请号：US14428031

申请日：2013-09-13

申请人： UNIVERSIDAD DE SEVILLA

发明人： Federico Paris Carballo ,  José Cañas Delgado ,  Jesús Justo Estebaranz ,  Damián Rivas Rivas ,  Antonio Franco Espín ,  Sergio Esteban Roncero ,  Francisco Gavilán Jiménez ,  Francisco Tinoco Franco

IPC分类号： B64C39/12 ,  B64C3/38 ,  B64C3/48 ,  B64C3/44

CPC分类号： B64C3/38 ,  B64C3/48 ,  B64C2003/445

摘要： Morphing aircraft wing with a mobile upper surface comprising a double skinning on the upper surface of the wing wherein one of the skinnings corresponds to the leading edge and the other corresponds to the trailing edge and they overlap in the central area of the wing with the possibility of relative displacement between the two skinnings and they extend in the direction of the chord of the wing profile, the wing comprises actuators that are positioned on the main wing spars and which exert a reaction force against said spars when they exert the force required to morph the wing displacing the skinnings in the direction of the chord of the profile to the configuration of low speed flight, take-off and landing.

公开(公告)号：US09481444B2

公开(公告)日：2016-11-01

申请号：US13611588

申请日：2012-09-12

申请人： Max U. Kismarton

发明人： Max U. Kismarton

IPC分类号： B64C3/26 ,  B64C3/20 ,  B64C3/18 ,  B64C3/44

CPC分类号： B64C3/26 ,  B64C3/18 ,  B64C3/20 ,  B64C2003/445 ,  Y02T50/14

摘要： An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending.

摘要翻译： 气动提升结构包括不平衡的复合皮肤，其耦合扭曲和弯曲。

公开(公告)号：US20150251747A1

公开(公告)日：2015-09-10

申请号：US14198012

申请日：2014-03-05

申请人： Toyota Motor Engineering & Manufacturing North America, Inc.

发明人： Robert W. Roe ,  Umesh N. Gandhi

IPC分类号： B64C3/14 ,  B64C3/44 ,  B64C3/54

CPC分类号： B64C3/44 ,  B64C3/54 ,  B64C2003/445 ,  B64C2003/543 ,  Y02T50/14 ,  Y10T29/49

摘要： An apparatus and methods for changing the shape of a wing using a trailing edge morphing beam. One example method includes coupling a trailing edge portion comprising a morphing beam to an elastic central portion of the wing. The morphing beam comprises a first portion formed of smart material and a second portion formed of elastic material. The method further includes actuating the smart material in the first portion of the morphing beam to change the shape of the elastic central portion of the wing and the elastic material of the morphing beam. The morphing beam can be configured to hold a first position corresponding to a minimum chord-length of the wing and a second position corresponding to a maximum chord length of the wing.

摘要翻译： 一种用于使用后缘变形光束来改变机翼的形状的装置和方法。 一个示例性方法包括将包括变形光束的后缘部分耦合到翼的弹性中心部分。 变形梁包括由智能材料形成的第一部分和由弹性材料形成的第二部分。 该方法还包括致动变形光束的第一部分中的智能材料以改变翼的弹性中心部分的形状和变形光束的弹性材料。 变形光束可以被配置为保持对应于翼的最小弦长的第一位置和对应于翼的最大弦长的第二位置。

公开(公告)号：US20150122951A1

公开(公告)日：2015-05-07

申请号：US14397990

申请日：2013-04-26

申请人： AIRBUS OPERATIONS LIMITED

发明人： Norman Wood

IPC分类号： B64C3/44

CPC分类号： B64C3/44 ,  B64C3/48 ,  B64C2003/445

摘要： A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil.

摘要翻译： 变形机翼包括：前缘; 后缘 以及在前缘和后缘之间延伸的上表面和下表面。 上部热致动构件设置在上表面附近; 并且下部热致动构件设置在与上部热致动器相对的下表面附近。 上部和下部热致动构件具有不同的热膨胀系数，并且被定位成使得当它们响应于环境温度的变化而膨胀或收缩不同的量从而使后缘发生偏转，从而改变机翼的弯度。

公开(公告)号：US08770523B2

公开(公告)日：2014-07-08

申请号：US12472770

申请日：2009-05-27

申请人： Rupert Pfaller

发明人： Rupert Pfaller

IPC分类号： B64C3/44

CPC分类号： B64C27/473 ,  B64C27/467 ,  B64C2027/4736

摘要： An aerodynamic profile (10) for aircraft, in particular for rotary wing aircraft, which profile (10) includes a cover skin (14, 15) on the pressure side and on the suction side, with a profile contour that is controllably formable in the rear profile region (13) by actuators (30), wherein each cover skin (14, 15) is designed as a non-shear-resistant sandwich that includes a film or foil (21, 22) which is connected to a non-shear-resistant core (20), wherein the cover skins (14, 15) are held in their profile shape by flexible webs (17).

摘要翻译： 用于飞行器，特别是用于旋翼飞机的空气动力学特性（10），其特征在于，所述轮廓（10）包括在所述压力侧和所述吸力侧上的盖皮肤（14,15），所述轮廓轮廓可控制地形成在 后部轮廓区域（13），其中每个覆盖皮肤（14,15）被设计为不耐剪切的夹心物，其包括连接到非剪切的膜或箔（21,22） （20），其中所述盖皮（14,15）通过柔性腹板（17）保持其轮廓形状。

公开(公告)号：US08382045B2

公开(公告)日：2013-02-26

申请号：US12506462

申请日：2009-07-21

申请人： David J. Manley ,  Robert E. Grip

发明人： David J. Manley ,  Robert E. Grip

IPC分类号： B64C3/44

CPC分类号： B64C3/48 ,  B64C9/16

摘要： A method and apparatus for controlling the shape of a control surface. A structure is rotated about an axis. The structure is located between a flexible skin and a skin located substantially opposite of the flexible skin. An assembly is moved to change the shape of the control surface in response to a rotation of the structure. The assembly is movably connected to the structure and is configured to move such that the flexible skin forms a plurality of curvatures.

摘要翻译： 一种用于控制控制表面形状的方法和装置。 一个结构围绕一个轴旋转。 该结构位于柔性皮肤和基本上与柔性皮肤相对的位置之间。 移动组件以响应于结构的旋转来改变控制表面的形状。 组件可移动地连接到结构，并且被配置为移动，使得柔性皮肤形成多个曲率。

公开(公告)号：US08366057B2

公开(公告)日：2013-02-05

申请号：US12843255

申请日：2010-07-26

申请人： Roelof Vos ,  Ronald M. Barrett

发明人： Roelof Vos ,  Ronald M. Barrett

IPC分类号： B64C3/46 ,  B64C3/44 ,  B64C3/52 ,  F01B19/00

CPC分类号： B64C3/46 ,  B64C3/50 ,  B64C11/20 ,  B64C2003/445 ,  Y02T50/14

摘要： A method and apparatus for an adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators. It is shown that two approaches can be taken to regulate the stiffness of this embedded actuator.

摘要翻译： 提出了一种适用于航空航天结构的方法和装置，其依赖于经过认证的航空航天材料，因此可用于常规客机。 该结构由细胞在垂直于细胞平面的显着长度上延伸的蜂窝材料组成。 当细胞形成完美的六边形时，每个细胞包含形成圆形管的非弹性袋（或膀胱）。 通过改变电池差压（CDP），蜂窝体的刚度可以改变。 使用外力或蜂窝状材料内的弹力，蜂窝体可以变形，使得细胞偏离其完美的六边形形状。 可以看出，通过增加CDP，结构最终返回到完美的六边形。 通过这样做，创建了一个完全嵌入的气动执行器，可以执行工作并代替传统的低带宽飞行控制执行器。 显示出可以采取两种方式来调节该嵌入式致动器的刚度。

公开(公告)号：US08262032B2

公开(公告)日：2012-09-11

申请号：US12616812

申请日：2009-11-12

申请人： Terry M. Sanderson ,  David R. Sar

发明人： Terry M. Sanderson ,  David R. Sar

IPC分类号： B64C3/48 ,  B64C3/44 ,  B64C3/56 ,  B64C3/00

CPC分类号： B64C3/185 ,  B64C3/48 ,  B64C3/56 ,  B64C2201/102

摘要： A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition.

摘要翻译： 诸如用于无人驾驶飞行器（UAV）的机翼的机翼包括可以从折叠状态选择性地扩展的梁或箱，以增加机翼的厚度。 梁可以包括一对板，当梁处于折叠状态时，彼此分离并将梁放置在膨胀状态下，它们靠近在一起。 板可以基本上彼此平行，并且在它们之间可以具有形状记忆泡沫和/或弹性装置，例如螺旋弹簧，以便在部署之前，期间和/或之后提供力分离板 机翼。 可膨胀/可折叠的梁可以具有锁定机构，以在梁处于膨胀状态时将其锁定到位。

公开(公告)号：US20120104181A1

公开(公告)日：2012-05-03

申请号：US12938352

申请日：2010-11-02

申请人： Matthew Boyd Rix

发明人： Matthew Boyd Rix

IPC分类号： B64C3/44

CPC分类号： B64C3/48 ,  B64C2003/445 ,  Y02T50/14

摘要： The present invention provides an apparatus, system, and method for morphing the cross-sectional shape of an airfoil between a high-speed, low-lift airfoil and a low-speed, high-lift airfoil, including interim airfoil configurations, to allow for optimal performance. This is done by inputting a control command into the system that alters the shape of the split or elastic upper and/or lower skin surface to allow the airfoil camber and chord to vary.

摘要翻译： 本发明提供了一种用于使翼型件的横截面形状变形在高速，低升程翼型和包括中间翼型构造的低速高升程翼型之间的装置，系统和方法，以允许 最佳性能。 这通过将系统中的控制命令输入到改变分裂或弹性上部和/或下部皮肤表面的形状以允许翼型弧度和弦变化来完成。

公开(公告)号：US08042772B2

公开(公告)日：2011-10-25

申请号：US12042443

申请日：2008-03-05

申请人： Kevin R. Lutke ,  Aaron J. Kutzmann

发明人： Kevin R. Lutke ,  Aaron J. Kutzmann

IPC分类号： B64C3/44

CPC分类号： B64C3/46

摘要： A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface.

摘要翻译： 用于翼型的飞行控制系统包括控制表面，将控制表面连接到翼型件的腔室以及与腔室流体连接的气动机构。 腔室可以由至少两个细胞构成，这些细胞可被膜流体地分离。 气动机构构造成为细胞提供差压以便交替地增加细胞的体积/压力以引起控制表面的偏转。 细胞可以具有可拉伸的外表面，以允许响应于细胞的充气/放气而改变外表面的长度。 电池的外表面可以与翼型件和控制表面的外部模具线基本上连续。