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。

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

CPC分类号： B64C1/00 ,  B64C3/10 ,  B64C15/02 ,  B64D27/18 ,  Y02T50/12 ,  Y02T50/44

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。

公开(公告)号：USD616804S1

公开(公告)日：2010-06-01

申请号：US29325636

申请日：2008-10-03

申请人： David J. Manley ,  Aaron J. Kutzmann ,  Robert D. Gregg, III ,  John C. Vassberg

设计人： David J. Manley ,  Aaron J. Kutzmann ,  Robert D. Gregg, III ,  John C. Vassberg

公开(公告)号：US08322655B1

公开(公告)日：2012-12-04

申请号：US12410865

申请日：2009-03-25

申请人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

发明人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

IPC分类号： B64C1/00

CPC分类号： B64C5/02

摘要： Apparatus and methods provide for an aircraft empennage that utilizes two torque tube members to create opposing sides of the empennage. The torque tube members are connected using a bridging member that is attached at opposing ends to the top portions of the torque tube members. The torque tube members and bridging member provide structural support for access cut-outs within the aircraft skin between the torque tube members for access to a payload space within. The torque tube members may include any number of walls, any of which may provide a pressure barrier to the payload space.

摘要翻译： 装置和方法为飞行器尾翼提供了利用两个扭矩管构件来产生尾翼的相对侧面的装置和方法。 扭矩管构件使用在相对端附接到扭矩管构件的顶部的桥接构件连接。 扭矩管构件和桥接构件提供用于在扭矩管构件之间的用于进入有效载荷空间的飞行器皮肤内的通路切口的结构支撑。 扭矩管构件可以包括任何数量的壁，其中任何一个可以为有效负载空间提供压力屏障。

公开(公告)号：US08353478B1

公开(公告)日：2013-01-15

申请号：US12410880

申请日：2009-03-25

申请人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

发明人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

IPC分类号： B64C1/00

CPC分类号： B64C1/26 ,  B64C9/38 ,  B64C2039/105 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars within the wings on each side of the aircraft may each be spliced into an aircraft frame that is part of the fuselage. The wing thickness provides mounting locations for aircraft engines and other components within the wing and passing through the wing spars. With this mid-wing configuration, the fuselage provides support for the various loads experienced by the wings without the use of a conventional structural wing box.

摘要翻译： 装置和方法为混合翼乘客或货机提供。 本公开的方面提供具有翼片的飞行器的飞行器，翼梁具有在机翼底部的厚度，其对应于机翼附接到的机身中的有效载荷空间的高度。 飞机每侧的机翼中的翼翼可以拼接成机身的一部分的飞机框架。 机翼厚度为机翼内的飞机发动机和其他部件提供安装位置，并穿过机翼翼梁。 凭借这种中翼配置，机身为不需要常规结构机翼的机翼的各种负载提供支持。

公开(公告)号：US08302908B1

公开(公告)日：2012-11-06

申请号：US13428095

申请日：2012-03-23

申请人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

发明人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

IPC分类号： B64C1/00

CPC分类号： B64C1/26 ,  B64C9/38 ,  B64C2039/105 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars within the wings on each side of the aircraft may each be spliced into an aircraft frame that is part of the fuselage. The wing thickness provides mounting locations for aircraft engines and other components within the wing and passing through the wing spars. With this mid-wing configuration, the fuselage provides support for the various loads experienced by the wings without the use of a conventional structural wing box.

摘要翻译： 装置和方法为混合翼乘客或货机提供。 本公开的方面提供具有翼片的飞行器的飞行器，翼梁具有在机翼底部的厚度，其对应于机翼附接到的机身中的有效载荷空间的高度。 飞机每侧的机翼中的翼翼可以拼接成机身的一部分的飞机框架。 机翼厚度为机翼内的飞机发动机和其他部件提供安装位置，并穿过机翼翼梁。 凭借这种中翼配置，机身为不需要常规结构机翼的机翼的各种负载提供支持。

公开(公告)号：US08226035B1

公开(公告)日：2012-07-24

申请号：US12410880

申请日：2009-03-25

申请人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

发明人： Max Kismarton ,  Aaron J. Kutzmann ,  Kevin Lutke

IPC分类号： B64C1/00

摘要： Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars within the wings on each side of the aircraft may each be spliced into an aircraft frame that is part of the fuselage. The wing thickness provides mounting locations for aircraft engines and other components within the wing and passing through the wing spars. With this mid-wing configuration, the fuselage provides support for the various loads experienced by the wings without the use of a conventional structural wing box.

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。

公开(公告)号：US08459591B2

公开(公告)日：2013-06-11

申请号：US13465220

申请日：2012-05-07

申请人： Kevin Reed Lutke ,  Aaron J. Kutzmann

发明人： Kevin Reed Lutke ,  Aaron J. Kutzmann

IPC分类号： B64F1/04

CPC分类号： B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/206

摘要： Methods and systems are provided which may allow a first vehicle to recover a second air vehicle while both are moving. The first vehicle and the second air vehicle may be traveling at different velocities. An attachment member of the second air vehicle may attach to a recovery member of the first vehicle while the first vehicle and the second air vehicle are traveling at different velocities. The recovery member attached to the second air vehicle may move relative to and along an exterior surface of the first vehicle in a direction substantially parallel to a direction of travel of the first vehicle.

摘要翻译： 提供了方法和系统，其可以允许第一车辆在移动时都恢复第二空中车辆。 第一车辆和第二空中车辆可以以不同的速度行驶。 当第一车辆和第二空中车辆以不同的速度行驶时，第二空中车辆的附接构件可以附接到第一车辆的回收构件。 附接到第二空气车辆的回收构件可以在与第一车辆的行进方向基本平行的方向上相对于第一车辆的外表面移动并沿其移动。

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。