公开(公告)号：US20130206917A1

公开(公告)日：2013-08-15

申请号：US13370314

申请日：2012-02-10

Applicant: Seiya Sakurai ,  Stephen J. Fox ,  Victor Reyes ,  Kara Marie Charles

Inventor： Seiya Sakurai ,  Stephen J. Fox ,  Victor Reyes ,  Kara Marie Charles

IPC: B64C3/50 ,  B64D45/00 ,  B64C13/30

CPC classification number: B64C9/22 ,  B64C9/24

Abstract: A system and method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap is disclosed. A sequence of flap positions is deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing position. The variable camber Krueger flap is positioned in a high position relative to a wing leading edge when the variable camber Krueger flap is fully deployed.

Abstract translation: 公开了一种使用可变外倾角Krueger瓣使流体动力体上的自然层流流动的系统和方法。 部署一系列的襟翼位置，其中可变弧度Krueger挡板在达到配置的起飞和着陆位置之前在机翼前缘的下方和后方。 当可变外倾角Krueger挡板完全展开时，可变弯度Krueger挡板相对于机翼前缘定位在较高的位置。

公开(公告)号：US20130075537A1

公开(公告)日：2013-03-28

申请号：US13242296

申请日：2011-09-23

Applicant: Seiya Sakurai ,  James M. Wheaton ,  Stephen J. Fox ,  Sharon Xiangdong Che

Inventor： Seiya Sakurai ,  James M. Wheaton ,  Stephen J. Fox ,  Sharon Xiangdong Che

IPC: B64C9/18 ,  B64C13/28

CPC classification number: B64C9/16 ,  Y02T50/32

Abstract: A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.

Abstract translation: 后缘翼片机构包括支撑梁，支撑气动翼片的翼片承载梁，互连第一和第二旋转点的第一连杆和互连第三和第四旋转点的第二连杆。 支撑梁在第一固定旋转轴线上具有接地连接。 连接链路在第二固定旋转轴线上具有接地连接，并且在第一和第二旋转点之间连接到第一连杆。 致动器与驱动连杆连接，该驱动连杆枢转地接合到第一连杆，用于使Fowler翼片的鼻部轮廓基本上平行于机翼下表面的初始向前和向后运动，具有延伸的后部运动，从而提供相对于翼片的快速变化的角度 机翼上表面。

公开(公告)号：US07815981B2

公开(公告)日：2010-10-19

申请号：US11384399

申请日：2006-03-21

Applicant: Hiroshi Iwanaga ,  Seiya Sakurai

Inventor： Hiroshi Iwanaga ,  Seiya Sakurai

IPC: C09K19/00

CPC classification number: H01L51/5253 ,  Y10T428/10 ,  Y10T428/1023 ,  Y10T428/1086 ,  Y10T428/2495 ,  Y10T428/24967 ,  Y10T428/2955 ,  Y10T428/3154 ,  Y10T428/31786

Abstract: A gas barrier film comprising a gas barrier laminate on a substrate film, wherein the gas barrier laminate comprises at least one three-layer unit consisting of a silicon nitride layer, a silicon oxynitride layer adjacent to the silicon nitride layer, and a silicon nitride layer adjacent to the silicon oxynitride layer. The gas barrier film has excellent transparency and gas barrier property.

Abstract translation: 一种阻气性膜，其在基材膜上具有阻气性叠层体，其特征在于，所述阻气性层压体包含至少一层由氮化硅层，与氮化硅层相邻的氮氧化硅层和氮化硅层构成的三层单元， 邻近氮氧化硅层。 阻气膜具有优异的透明性和阻气性。

公开(公告)号：US07744040B2

公开(公告)日：2010-06-29

申请号：US12264831

申请日：2008-11-04

Applicant: Douglas S. Lacy ,  Kevin W. Beyer ,  Stephen T. Brown ,  Paul W. Dees ,  Neal V. Huynh ,  Jan A. Kordel ,  Clayton A. Prow ,  Seiya Sakurai

Inventor： Douglas S. Lacy ,  Kevin W. Beyer ,  Stephen T. Brown ,  Paul W. Dees ,  Neal V. Huynh ,  Jan A. Kordel ,  Clayton A. Prow ,  Seiya Sakurai

IPC: B64C3/50

CPC classification number: B64C9/16 ,  B64C2009/143

Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

Abstract translation: 公开了包括具有非平行运动路径的装置和相关方法的飞行器后缘装置。 根据一个实施例的装置包括机翼和内侧后缘装置，其联接到机翼并且可沿着第一运动路径在第一收起位置和第一展开位置之间相对于机翼移动。 外侧后缘装置可以联接到内侧后缘装置的翼外侧，并且可以沿着不平行于第一运动路径的第二运动路径相对于机翼移动。 中间后缘装置可以联接在内侧和后侧后缘装置之间，并且可以沿着不平行于第一和第二运动路径的第三运动路径移动。 每个后缘装置可以在移动到它们各自的展开位置时相对于机翼打开间隙。

公开(公告)号：US20100140414A1

公开(公告)日：2010-06-10

申请号：US12331193

申请日：2008-12-09

Applicant: Kevin W. Beyer ,  Seiya Sakurai

Inventor： Kevin W. Beyer ,  Seiya Sakurai

IPC: B64C3/50 ,  B64D15/02

CPC classification number: B64C9/24 ,  B64C9/22 ,  Y02T50/32

Abstract: Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil forming a base link. The system further includes a six-bar linkage coupled to the airfoil and having a Stephenson II configuration, including a binary second link pivotably connected to the airfoil, a ternary third link pivotably connected to the second link, a binary fourth link pivotably connected to the third link, a ternary fifth link pivotably connected to the airfoil and the fourth link, and a binary sixth link pivotably connected to the third link and the fifth link. The system can further include a deployable leading edge panel carried by the linkage, with the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.

Abstract translation: 公开了包括用于多位置襟翼的斯蒂芬森II链接机构和相关系统和方法的链接机构。 根据特定实施例的系统包括具有外部流动表面的机翼，其具有上部和下部，并且翼型形成基部连杆。 该系统还包括联接到翼型件并具有斯蒂芬森II构造的六杆连杆，其包括可枢转地连接到翼型件的二元第二连杆，可枢转地连接到第二连杆的三元第三连杆，可枢转地连接到第二连杆的二进制第四连杆 第三连杆，可枢转地连接到翼型件和第四连杆的三元第五连杆，以及可枢转地连接到第三连杆和第五连杆的二元第六连杆。 所述系统还可以包括由所述联动装置承载的可展开的前缘面板，所述前缘面板可通过所述连接件在收起位置与至少一个展开位置之间移动。

公开(公告)号：US07611099B2

公开(公告)日：2009-11-03

申请号：US11220446

申请日：2005-09-07

Applicant: Jan A. Kordel ,  Seiya Sakurai ,  Bret A. Bowers ,  Christopher G. Glassmoyer ,  Darren B. Williams

Inventor： Jan A. Kordel ,  Seiya Sakurai ,  Bret A. Bowers ,  Christopher G. Glassmoyer ,  Darren B. Williams

IPC: B64C3/50

CPC classification number: B64C7/00 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/32 ,  Y10S277/916

Abstract: Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

Abstract translation: 这里描述了用于与飞机上的控制表面一起使用的气动密封件。 在一个实施例中，与飞行器一起使用的密封组件包括第一密封构件和第二密封构件。 第一密封构件具有构造成附接到飞机的固定翼型部分的第一近端部分，以及构造成从固定翼型部分朝向可移动控制表面向外延伸的第一远端部分。 第二密封构件具有构造成附接到可移动控制表面的第二近端部分，以及被配置为从控制表面朝向固定翼型部分向外延伸的第二远端部分。 在该实施例中，第二远端部分进一步构造成当控制表面相对于固定翼型部分移动时，可移动地接触第一远端部分以至少部分地密封固定翼型部分和可移动控制表面之间的间隙。

公开(公告)号：US20090146016A1

公开(公告)日：2009-06-11

申请号：US12001414

申请日：2007-12-11

Applicant: Jan A. Kordel ,  Seiya Sakurai ,  Michael A. Balzer ,  John V. Dovey

Inventor： Jan A. Kordel ,  Seiya Sakurai ,  Michael A. Balzer ,  John V. Dovey

IPC: B64C3/50

CPC classification number: B64C9/02 ,  B64C9/16 ,  Y02T50/32 ,  Y02T50/44

Abstract: Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other. A cam is carried by the other of the wing and trailing edge device and is positioned within the cam track between the opposing cam track surfaces. The cam is offset from the pivot axis and during normal operation the cam can carry no load or a first load along a load path that includes the cam track, and when a decrease in support provided by at least one of the pivot element, the wing support and the device support occurs, the cam can carry a second non-zero load greater than the first load along the load path.

Abstract translation: 公开了追尾设备捕获器和相关联的系统和方法。 根据一个实施例的系统包括具有机翼支撑件的机翼，后缘装置，其相对于机翼承载并可移动并具有装置支撑件，以及连接在机翼和后缘装置之间的联轴器。 联接器可以包括枢转接头，其包括枢转元件，该枢转元件沿枢转轴线对准并且连接在机翼支撑件和设备支撑件之间。 联接器还可以包括联接在翼和后缘装置之间的致动器，其中致动器具有第一位置，在该第一位置中后缘装置被收起，以及第二位置，其中后缘装置被展开，其中空气流 当后缘装置处于第二位置时，位于翼和后缘装置之间的间隙。 凸轮轨道由机翼和后缘装置中的一个承载，并且具有相对于彼此固定的相对的凸轮轨道表面。 凸轮由翼和后缘装置中的另一个承载，并且位于相对的凸轮轨道表面之间的凸轮轨道内。 凸轮偏离枢转轴线，并且在正常操作期间，凸轮可以沿着包括凸轮轨道的负载路径承载负载或第一负载，并且当至少一个枢轴元件，翼片 支撑和设备支撑发生，凸轮可以承载大于沿着负载路径的第一负载的第二非零负载。

公开(公告)号：US20090072093A1

公开(公告)日：2009-03-19

申请号：US11453596

申请日：2006-06-14

Applicant: Stephen J. Fox ,  Seiya Sakurai

Inventor： Stephen J. Fox ,  Seiya Sakurai

IPC: B64C3/50

CPC classification number: B64C9/22 ,  Y02T50/32 ,  Y02T50/44

Abstract: Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly that in turn includes a deployable leading edge panel having a generally fixed-shape flow surface, a bullnose coupled to the panel, and a link mechanism coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism can include a first support link, a second support link, and first, second, and third positioning links. The positioning links can be pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap with the airfoil when in the deployed position. The positioning links can be the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.

Abstract translation: 公开了用于间隙刚性克鲁格襟翼的链接机构，以及相关联的方法和系统。 根据一个实施例的系统包括可展开的前缘组件，其还包括具有大致固定形状的流动表面的可展开的前缘面板，联接到面板的大斗杆，以及连接到面板和牛仔的连杆机构 在收起位置和展开位置之间移动面板。 该机构可以包括第一支撑连杆，第二支撑连杆以及第一，第二和第三定位连杆。 定位连杆可以在前缘面板，牛角，第一支撑连杆和第二支撑连杆之间可枢转地连接，使得当处于展开位置时，前缘面板与翼型件形成间隙。 定位连杆可以是在特定的机翼跨度位置处联接在支撑连杆，前缘面板和长臂之间的唯一定位连杆。

公开(公告)号：US20080124534A1

公开(公告)日：2008-05-29

申请号：US11663090

申请日：2005-09-09

Applicant: Seiya Sakurai ,  Hirohisa Hokazono

Inventor： Seiya Sakurai ,  Hirohisa Hokazono

IPC: C08G69/32 ,  B32B7/02 ,  B32B9/00

CPC classification number: C08G69/32 ,  C08G69/26 ,  C08G69/265 ,  C08J5/18 ,  C08J2377/10

Abstract: A polyamide having from 25 to 90 mol % of a repeating unit of the following formula (1) and having from 10 to 75 mol % of a repeating unit of the following formula (2): formula (1) formula (2) wherein the ring and the ring are a monocyclic or polycyclic ring; R1 and R2 each are H or a substituent; R3 and R4 each are a substituent; p and q each are from 0 to 4; and L is 2,6-naphthylene, 3,3′-biphenylene or paraphenylene. The polyamide has good heat resistance and excellent optical and mechanical properties.

Abstract translation: 具有25〜90摩尔％的下式（1）的重复单元并具有10〜75摩尔％的下式（2）的重复单元的聚酰胺：式（1）式（2）其中， 环和环是单环或多环; R 1和R 2各自为H或取代基; R 3和R 4各自为取代基; p和q各自为0至4; L是2,6-亚萘基，3,3'-亚联苯基或对亚苯基。 聚酰胺具有良好的耐热性和优异的光学和力学性能。

公开(公告)号：US20070252040A1

公开(公告)日：2007-11-01

申请号：US11220446

申请日：2005-09-07

Applicant: Jan Kordel ,  Seiya Sakurai ,  Bret Bowers ,  Christopher Glassmoyer ,  Darren Williams

Inventor： Jan Kordel ,  Seiya Sakurai ,  Bret Bowers ,  Christopher Glassmoyer ,  Darren Williams

IPC: B64C3/00

CPC classification number: B64C7/00 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/32 ,  Y10S277/916

Abstract: Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

Abstract translation: 这里描述了用于与飞机上的控制表面一起使用的气动密封件。 在一个实施例中，与飞行器一起使用的密封组件包括第一密封构件和第二密封构件。 第一密封构件具有构造成附接到飞机的固定翼型部分的第一近端部分，以及构造成从固定翼型部分朝向可移动控制表面向外延伸的第一远端部分。 第二密封构件具有构造成附接到可移动控制表面的第二近端部分，以及被配置为从控制表面朝向固定翼型部分向外延伸的第二远端部分。 在该实施例中，第二远端部分进一步构造成当控制表面相对于固定翼型部分移动时，可移动地接触第一远端部分以至少部分地密封固定翼型部分和可移动控制表面之间的间隙。