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1.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：US08317129B1
公开(公告)日：2012-11-27
申请号：US12410828
申请日：2009-03-25
申请人： Edward Lawson , Aaron J. Kutzmann
发明人： Edward Lawson , Aaron J. Kutzmann
IPC分类号： B64B1/24
CPC分类号： B64D27/18 , B64C2039/105 , B64D33/04 , F02K1/00 , F05D2250/323 , Y02T50/12 , Y02T50/44 , Y02T50/672
摘要： Apparatus and methods provide for an engine nozzle having a universal convergent nozzle and a distinct nozzle aperture. Aspects of the disclosure provide a universal convergent nozzle that includes a nozzle throat and is attachable at a first end to an aircraft engine and at a second end to a distinct nozzle aperture. While the distinct nozzle aperture may include features that are specific to the corresponding engine mounting location, the universal convergent nozzle may be interchangeably used with any engine and distinct nozzle aperture at any engine mounting location. The configuration of the universal convergent nozzle ensures consistent engine performance and engine exhaust plume conditioning across all engine mounting locations, irrespective of the distinct nozzle aperture features downstream of the universal convergent nozzle.
摘要翻译： 装置和方法提供了具有通用会聚喷嘴和不同喷嘴孔的发动机喷嘴。 本公开的方面提供了一种通用会聚喷嘴，其包括喷嘴喉部，并且可在第一端附接到飞行器发动机，并且在第二端附接到不同的喷嘴孔。 虽然不同的喷嘴孔口可以包括特定于相应的发动机安装位置的特征，但是在任何发动机安装位置处，通用会聚喷嘴可以与任何发动机和不同的喷嘴孔口互换使用。 通用会聚喷嘴的配置确保了所有发动机安装位置的引擎性能和发动机排气羽流调节，而不管通用会聚喷嘴下游具有不同的喷嘴孔特征。
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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：US08459591B2
公开(公告)日：2013-06-11
申请号：US13465220
申请日：2012-05-07
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。
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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：US06926231B2
公开(公告)日：2005-08-09
申请号：US10829757
申请日：2004-04-22
CPC分类号： F02K7/075 , B64C1/1415 , B64C29/0058 , B64D5/00 , B64D27/023 , B64D27/20 , Y02T50/44 , Y02T50/672
摘要： A method is provided for reducing vulnerability to hostile detection of and aggression towards an aircraft. The method includes adapting an aircraft fuselage to form an armored payload bay, wherein the armored payload bay includes a pair of sidewalls and a bottom. The method additionally includes adapting wings of the aircraft to allow the aircraft to be transported within a larger aircraft. For example, the wings could have a fixed wing span that allows the aircraft to transported within a larger aircraft or the wings could be adapted to fold so that the aircraft can transported within a larger aircraft. The method further includes disposing at least one pulse ejector thrust augmentor (PETA) bank within each sidewall. Each PETA bank is oriented such that a thrust exhaust produced is directed down and away from a centerline of the payload bay. Still further, the method includes adapting the bottom of payload bay to allow ingress and egress of cargo.
摘要翻译： 提供了一种减少对飞机的敌对侦察和侵略的脆弱性的方法。 该方法包括使飞行器机身适应形成装甲有效载荷舱，其中装甲有效载荷舱包括一对侧壁和底部。 该方法还包括使飞行器的翼适应，以允许飞机在较大的飞机内运输。 例如，机翼可以具有固定的机翼跨度，其允许飞机在更大的飞行器内运输，或者翼可以适应折叠，使得飞机可以在更大的飞机内运输。 该方法还包括在每个侧壁内设置至少一个脉冲喷射推力增强器（PETA）组。 每个PETA组被定向成使得产生的推力排气向下并远离有效载荷舱的中心线。 此外，该方法包括调整有效载荷底部以允许货物的入口和出口。
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7.发明授权Projectile and associated method for seeking a target identified by laser designation 有权用于寻找通过激光识别识别的目标的弹丸和相关方法公开(公告)号：US08829401B1
公开(公告)日：2014-09-09
申请号：US13162167
申请日：2011-06-16
申请人： Kevin Lutke , Aaron J. Kutzmann
发明人： Kevin Lutke , Aaron J. Kutzmann
摘要： A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.
摘要翻译： 提供射弹和相关方法用于寻求已经被激光指定的目标，即使射弹不包括激光接收器。 射弹包括空气动力体和GPS接收器，其被配置为接收指示空气动力体的位置的GPS信号。 射弹还包括无线电接收器，其被配置为从外部激光接收机接收无线电信号，所述无线电信号基于目标的激光指定来提供与目标的位置有关的信息。 此外，射弹包括处理器，其被配置为基于根据由GPS信号确定的空气动力学体的位置和基于由外侧激光接收器提供的信息的目标的位置来引导空气动力学体向目标的飞行。
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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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公开(公告)号：US20120211588A1
公开(公告)日：2012-08-23
申请号：US13465220
申请日：2012-05-07
IPC分类号： B64D5/00
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。
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公开(公告)号：US07900866B2
公开(公告)日：2011-03-08
申请号：US11874804
申请日：2007-10-18
申请人： Aaron J. Kutzmann , Kevin R. Lutke
发明人： Aaron J. Kutzmann , Kevin R. Lutke
IPC分类号： B64D5/00
CPC分类号： B64D3/00 , B64C39/024 , B64C2201/082 , B64C2201/182 , B64D5/00
摘要： A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to enable the aircraft to translate along the flexible tether. In embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether.
摘要翻译： 飞机机载发射和恢复的系统和方法。 在一个实施例中，系统包括被配置为被拖到空中母舰后面的柔性系绳。 牵引装置固定到柔性系绳的远端以产生阻力并保持柔性系绳中的张力。 与母船相关联的卷轴锚定柔性系绳的近端部分，并且选择性地放出并吸收柔性系绳以调节柔性系绳的长度。 与飞行器相关联的捕获机构接合柔性系绳，以使飞机沿着柔性系绳平移。 在本方法的实施例中，从空中母舰部署柔性系绳。 飞机沿着柔性系绳向前和向后平移。 在发射之前，飞机的重量从柔性系绳转移到机翼。 在恢复期间，飞机的重量从翼转移到柔性系绳。
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