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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
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。
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公开(公告)号：US20110017876A1
公开(公告)日：2011-01-27
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
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。
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公开(公告)号：US07635107B2
公开(公告)日：2009-12-22
申请号：US11200515
申请日：2005-08-09
IPC分类号： B64C21/04
CPC分类号： B64C9/16 , B64C9/22 , B64C21/02 , B64C21/04 , B64C2230/04 , B64C2230/06 , Y02T50/166 , Y02T50/32
摘要： A system and method for controlling boundary layer flow over an aircraft wing are provided. The system includes at least one wing element, and a plurality of ports defined in the wing element and in fluid communication with one another. The system also includes at least one fluidic device operable to continuously ingest the fluid through at least one of the ports and eject the fluid out of at least one other port to control boundary layer flow of the fluid over the wing element.
摘要翻译： 提供一种用于控制飞机机翼上的边界层流动的系统和方法。 该系统包括至少一个翼元件和限定在翼元件中并且彼此流体连通的多个端口。 该系统还包括至少一个流体装置，其可操作以通过至少一个端口连续摄取流体并将流体从至少一个其它端口排出，以控制流体在翼元件上的边界层流动。
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公开(公告)号：US08403256B1
公开(公告)日：2013-03-26
申请号：US12410894
申请日：2009-03-25
申请人： Robert D Gregg, III , Aaron J. Kutzmann , David J. Manley , John C. Vassberg , Neal Harrison , Max Kismarton
发明人： Robert D Gregg, III , Aaron J. Kutzmann , David J. Manley , John C. Vassberg , Neal Harrison , Max Kismarton
IPC分类号： B64C39/12
CPC分类号： B64C1/061 , B64C3/10 , B64C9/38 , B64C2001/0045 , B64C2039/105 , Y02T50/12 , Y02T50/32 , Y02T50/44
摘要： Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system.
摘要翻译： 装置和方法提供了扫掠式动力升降飞机。 本公开的方面提供了一种动力升降飞行器，其利用在上表面吹风襟翼上的发动机排气流，以在各种飞行操作期间增加升力。 动力升降飞机具有内侧部分和外侧部分的翼。 相邻的内侧和外侧部分共享一个扫掠的前缘。 前缘被扫掠到将外侧部分向后移动到在升降系统的启动或停用时电梯的中心几乎没有变化的位置的程度。
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5.发明授权Aircraft configuration utilizing fuselage, wing, empennage, and exhaust flow control devices 有权飞机配置采用机身，机翼，尾翼和排气流量控制装置公开(公告)号：US08061655B1
公开(公告)日：2011-11-22
申请号：US12410813
申请日：2009-03-25
申请人： David J. Manley , Aaron J. Kutzmann , Robb Gregg, III , John C. Vassberg , Antonio B. Gonzales , Steve Hollowell , Neal Harrison , Edward Lawson , Max Kismarton , Kevin Lutke
发明人： David J. Manley , Aaron J. Kutzmann , Robb Gregg, III , John C. Vassberg , Antonio B. Gonzales , Steve Hollowell , Neal Harrison , Edward Lawson , Max Kismarton , Kevin Lutke
IPC分类号： B64C1/00
摘要： Apparatus and methods provide for an aircraft configuration that utilize structural and engine exhaust flow control devices to enhance performance. Aspects of the disclosure provide a fuselage with a pressure vessel nested within a non-cylindrical outer mold line fairing. A twin-boom empennage may be connected to the fuselage. A wing may attach in a blended wing configuration with a sweep angle that positions the aircraft center of lift to minimize any pitching moment induced by the activation or deactivation of an upper surface blown (USB) system. The USB system may include a conformal USB flap positioned downstream of an engine exhaust plume, as well as a controllable USB nozzle aperture to promote exhaust flow attachment to the conformal USB flap. A universal convergent nozzle may be utilized to connect each controllable USB nozzle aperture to a corresponding internally mounted aircraft engine.
摘要翻译： 装置和方法提供了利用结构和发动机排气流量控制装置来增强性能的飞行器配置。 本公开的方面提供了一种具有嵌套在非圆柱形外模线整流罩内的压力容器的机身。 机身可能连接双桅杆尾翼。 翼可以以具有扫掠角的混合翼构型附接，该倾斜角定位飞行器的升降机中心，以最小化由上表面吹（USB）系统的激活或停用引起的任何俯仰时刻。 USB系统可以包括位于发动机排气羽流下游的共形USB挡板以及可控制的USB喷嘴孔，以促进附着到保形USB挡板的排气流。 可以使用通用会聚喷嘴将每个可控USB喷嘴孔连接到相应的内部安装的飞机发动机。
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公开(公告)号：US20080173766A1
公开(公告)日：2008-07-24
申请号：US11828437
申请日：2007-07-26
申请人： David J. Manley
发明人： David J. Manley
CPC分类号： B64C21/08 , B64C21/04 , B64C2230/04 , Y02T50/166
摘要： The present invention is directed to a distributed active flow control (“DAFC”) system that maintains attached airflow over a highly cambered airfoil employed by an aircraft or other similar applications. The DAFC system includes a primary power source comprised of one or more aircraft engines, one or more power conversion units, and optionally, one or more auxiliary power units. The power conversion units are coupled to one or more aircraft engines for supplying power to a distribution network. The distribution network disperses power from the one or more power conversion units to active flow control units disposed within one or more aircraft flight control surfaces (e.g., the aircraft wing, the tail, the flaps, the slats, the ailerons, and the like). In one embodiment, an auxiliary power unit is included for providing a redundant and auxiliary power supply to the distribution network. In another embodiment, a back-up power source is provided in communication with the distribution network for providing an additional redundant power supply.
摘要翻译： 本发明涉及一种分布式主动流量控制（“DAFC”）系统，其将附着的气流保持在航空器或其它类似应用所使用的高度弧形的翼型上。 DAFC系统包括由一个或多个飞机发动机，一个或多个功率转换单元和可选地一个或多个辅助动力单元组成的主电源。 功率转换单元耦合到一个或多个飞行器发动机，用于向分配网络供电。 分配网络将功率从一个或多个功率转换单元分散到设置在一个或多个飞行器飞行控制表面内的主动流量控制单元（例如飞行器机翼，尾翼，翼片，板条，副翼等） 。 在一个实施例中，包括用于向分配网络提供冗余和辅助电源的辅助电源单元。 在另一个实施例中，备用电源与分配网络通信以提供额外的冗余电源。
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公开(公告)号：USD616804S1
公开(公告)日：2010-06-01
申请号：US29325636
申请日：2008-10-03
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8.发明授权
公开(公告)号：US6078593A
公开(公告)日：2000-06-20
申请号：US795184
申请日：1997-02-04
申请人： Thomas R. Eames , Lac X. Trinh , E. Barton Manchester , Bradley N. Yearwood , David J. Manley , Scott T. Hicks , Jaskarn S. Johal , Charles A. Eldering
发明人： Thomas R. Eames , Lac X. Trinh , E. Barton Manchester , Bradley N. Yearwood , David J. Manley , Scott T. Hicks , Jaskarn S. Johal , Charles A. Eldering
CPC分类号： H04Q11/0478 , H04J2203/0032 , H04J2203/0089
摘要： A fiber to the curb communication system providing telephone service to subscribers using line cards which are pluggable into a broadband network unit. The line cards provide telephone service to up to six lines per card. The cards are programmable from a central location, and the system includes self-testing of the cards, ring generator testing and provides for testing of the telephone lines from the system to the subscriber's location.
摘要翻译： 路由通信系统的光纤提供使用可插入宽带网络单元的线路卡的用户的电话服务。 线卡提供电话服务，每张卡多达六行。 这些卡可以从中央位置编程，并且系统包括卡的自检，环形发生器测试，并提供从系统到用户位置的电话线路的测试。
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