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131.发明授权公开(公告)号：US09120554B2
公开(公告)日：2015-09-01
申请号：US13210375
申请日：2011-08-16
CPC分类号： B64C3/48 , B64C2003/445 , Y10T29/49826
摘要： A system and methods for configuring a fluid-dynamic body is disclosed. A camber of a fluid-dynamic body is configured by activating a shape memory alloy actuator coupled to the fluid-dynamic body.
摘要翻译： 公开了一种用于配置流体动力体的系统和方法。 通过激活耦合到流体动力体的形状记忆合金致动器构造流体动力体的弯度。
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公开(公告)号：US08783625B2
公开(公告)日：2014-07-22
申请号：US13267614
申请日：2011-10-06
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。
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公开(公告)号：US08678324B2
公开(公告)日：2014-03-25
申请号：US12918408
申请日：2009-02-20
申请人： Christopher Douglas Hemmelgarn , Bryan Michael Pelley , Kristin Marie Cable , Brandon Charles Kirby
发明人： Christopher Douglas Hemmelgarn , Bryan Michael Pelley , Kristin Marie Cable , Brandon Charles Kirby
CPC分类号： B64C3/48 , B64C2003/445 , F03D1/0675 , F05B2240/311 , Y02E10/721 , Y02T50/14
摘要： Embodiments of the present airfoil systems comprise an airfoil with a leading edge, a trailing edge, an upper surface, a lower surface, and a skin surface, at least one structural element located within said airfoil, wherein said structural element supports the skin surface having an upper skin portion and a lower skin portion wherein said structural element can change its shape in response to external stimulus during flight operations, and an actuating means for selectively altering the curvature of said structural element which alters the curvature of said upper skin portion and of said lower skin portion to cause nonlinear deflection of said skin surface between an extreme raised position through a neutral position to an extreme lowered position; whereby the outer surface curvature of said airfoil and said skin surface is smooth and continuous over substantially the entirety thereof at all positions of said skin surface.
摘要翻译： 本翼型系统的实施例包括具有前缘，后缘，上表面，下表面和皮肤表面的翼型件，位于所述翼型内的至少一个结构元件，其中所述结构元件支撑具有 上皮肤部分和下皮肤部分，其中所述结构元件可以响应于飞行操作期间的外部刺激而改变其形状;以及致动装置，用于选择性地改变改变所述上皮肤部分的曲率的所述结构元件的曲率， 所述下部皮肤部分引起所述皮肤表面在通过中性位置的极端升高位置到极端降低位置之间的非线性偏转; 由此在所述皮肤表面的所有位置处，所述翼型件和所述皮肤表面的外表面曲率在其基本上整体上平滑且连续。
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公开(公告)号：US20130099063A1
公开(公告)日：2013-04-25
申请号：US13276750
申请日：2011-10-19
CPC分类号： B64D27/24 , B64C3/18 , B64C3/182 , B64C3/185 , B64C3/187 , B64C3/22 , B64C3/26 , B64D2211/00 , Y02T50/44 , Y02T50/62 , Y02T50/64 , Y10T156/10
摘要： An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature.
摘要翻译： 飞机机翼具有多个翼段，其通过接头安装在翼梁上，允许翼梁和翼段之间的相对运动。 采用热膨胀系数的调整来减少温度变化引起的应力。
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公开(公告)号：US08418967B2
公开(公告)日：2013-04-16
申请号：US12859966
申请日：2010-08-20
CPC分类号： B64C3/48 , B64C2003/445 , F03D1/0675 , F05B2240/301 , F05B2240/31 , F05B2240/311 , Y02E10/721 , Y02T50/14
摘要： Embodiments of the present airfoil structural insert comprise an airfoil structural insert frame, a skin surface disposed about the airfoil structural insert frame, at least one attachment point operable for coupling to an aerodynamic structure, a leading edge disposed on one end of the airfoil structural insert frame, a trailing edge disposed on an opposite end of the airfoil structural insert frame, and at least one structural element configured to support the skin surface, wherein said structural element undergoes at least one nonlinear shape change from a first shape to a deflected shape.
摘要翻译： 本翼型结构插入件的实施例包括翼型结构插入框架，围绕翼型结构插入框架设置的皮肤表面，可操作以联接到空气动力学结构的至少一个附接点，设置在翼型结构插入件的一端的前缘 框架，设置在翼型结构插入框架的相对端上的后缘，以及构造成支撑皮肤表面的至少一个结构元件，其中所述结构元件经历从第一形状到偏转形状的至少一个非线性形状的变化。
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公开(公告)号：US20120104182A1
公开(公告)日：2012-05-03
申请号：US13267614
申请日：2011-10-06
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。
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公开(公告)号：US20120061523A1
公开(公告)日：2012-03-15
申请号：US13178533
申请日：2011-07-08
申请人： Tamas Havar , Oliver Meyer , York C. Roth , Oliver Seack
发明人： Tamas Havar , Oliver Meyer , York C. Roth , Oliver Seack
CPC分类号： B64C9/24
摘要： Embodiments of the invention relate to an aerodynamic body with an extension in the spanwise direction, wing chord direction and wing thickness direction for coupling to a wing of an aircraft. This aerodynamic body can here be used for a leading edge flap or slat of an aircraft wing. To improve the flow characteristics, the rear side of the aerodynamic body is provided with a skin section that can be molded between a convex curvature and concave curvature.
摘要翻译： 本发明的实施例涉及一种空气动力学主体，其在翼展方向上延伸，翼弦方向和翼厚度方向用于联接到飞行器的翼。 这种空气动力学体在这里可以用于飞机机翼的前缘皮瓣或缝翼。 为了改善流动特性，空气动力体的后侧设置有能够在凸曲率和凹曲率之间模制的皮肤部分。
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公开(公告)号：US07963485B2
公开(公告)日：2011-06-21
申请号：US12307619
申请日：2007-07-10
申请人： Manfred Koneczny
发明人： Manfred Koneczny
IPC分类号： B64C3/44
摘要： A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile.
摘要翻译： 在飞行器的机身附近提供可调节的水平稳定器，并且具有预定的空气动力学特性。 可移动电梯设置成与水平稳定器相邻。 水平稳定器具有承载结构，其在跨度方向上延伸并牢固地连接到飞行器的机身，以及可移动区域，其连接到承载结构，使得它们可以移动并且可以独立于 电梯，以便通过改变空气动力学特性来修剪水平稳定器。
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139.发明授权Wing unit, in particular spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units or rudder units of a plane 有权翼单元，特别是翼梁箱，用于形成飞机的空气动力学活动表面，特别是飞机的翼型，水平尾翼单元或舵单元公开(公告)号：US07909292B2
公开(公告)日：2011-03-22
申请号：US12560679
申请日：2009-09-16
申请人： Barnaby Law
发明人： Barnaby Law
IPC分类号： B64C3/44
摘要： The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane.Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit.
摘要翻译： 本发明涉及一种机翼单元，特别是用于形成飞行器，特别是平面的翼型，水平尾翼单元或舵单元的空气动力学活动表面的翼梁箱。 由于空气动力学活动表面的表面几何形状，可以获得空气动力学改进，该表面几何形状通过使用致动构件适应于平面的相应操作状态和/或由于机翼单元的结构机械负载的最小化而导致的重量节省 。
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140.发明授权Joint for connecting a longitudinal side to an upper side of components and flexible strip for use in such a joint 有权用于将纵向侧面连接到组件的上侧的接头和用于这种接头中的柔性带公开(公告)号：US07900878B2
公开(公告)日：2011-03-08
申请号：US12286690
申请日：2008-09-30
申请人： Juan Perez-Sanchez
发明人： Juan Perez-Sanchez
CPC分类号： B64C9/02 , F16C11/12 , Y10T16/525 , Y10T16/5257 , Y10T403/35 , Y10T403/7062
摘要： A joint arrangement connects a longitudinal edge of a first component with an upper surface of a second component. At least two cooperating bands are secured with their first ends respectively on opposite sides of the first component, and are secured with their second ends respectively on clamping elements arranged on the second component, so that the bands intersect the major center plane of the first component in the joint area between the components. A pressure element is positioned on at least one clamping element for supporting the first component, and the bands extend laterally next to the pressure element and crosswise relative to one another.
摘要翻译： 联合装置将第一部件的纵向边缘与第二部件的上表面连接。 至少两个配合带的第一端分别固定在第一部件的相对侧上，并且其第二端分别固定在布置在第二部件上的夹紧元件上，使得带与第一部件的主中心平面交叉 在组件之间的联合区域。 压力元件定位在用于支撑第一部件的至少一个夹紧元件上，并且该带横向延伸靠近压力元件并相对于彼此横向延伸。
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