公开(公告)号：US20110112878A1

公开(公告)日：2011-05-12

申请号：US12939596

申请日：2010-11-04

申请人： Joshua D. Isom ,  James P. Cycon ,  Erez Eller ,  Mark W. Davis

发明人： Joshua D. Isom ,  James P. Cycon ,  Erez Eller ,  Mark W. Davis

IPC分类号： G06Q10/00 ,  G06F19/00

CPC分类号： G07C5/006 ,  G05B23/024 ,  G05B23/0283 ,  G06Q10/06311 ,  G07C5/008 ,  G07C5/0841

摘要： A computer-implemented method, system, and computer program product for virtual monitoring of aircraft fleet loads are provided. The method includes calculating virtual load data associated with an aircraft from a set of orthogonal waveforms. The method also includes calculating a set of coefficients as a function of parametric data and high frequency data associated with an aircraft. The method further includes storing the set of coefficients on the aircraft and transmitting the set of coefficients to a ground-based system configured to reproduce the virtual load data based on a copy of the set of orthogonal waveforms and the received set of coefficients in order to perform aircraft fleet management.

摘要翻译： 提供了一种用于虚拟监控飞机机队负载的计算机实现的方法，系统和计算机程序产品。 该方法包括从一组正交波形计算与飞行器相关联的虚拟负载数据。 该方法还包括计算作为参数数据和与飞行器相关联的高频数据的函数的一系列系数。 该方法还包括将该系数集合存储在飞行器上，并将该系数集合发送到基于地面的系统，该地面系统被配置为基于该组正交波形的副本和所接收的一系列系数再现虚拟负载数据，以便 执行飞机机队管理。

公开(公告)号：US07984146B2

公开(公告)日：2011-07-19

申请号：US11417465

申请日：2006-05-04

申请人： James N. Rozak ,  James P. Cycon

发明人： James N. Rozak ,  James P. Cycon

IPC分类号： G06F15/173 ,  G01M17/00

CPC分类号： G06Q50/30 ,  G06Q10/06 ,  G08G5/0013 ,  H04L67/02 ,  H04L67/125

摘要： A Health and Usage Monitoring System (HUMS) utilizes a common architecture which permits OEM and rotorcraft operators to view and trend HUMS data for an entire aircraft fleet independent of aircraft model, HUMS vendor, or raw data format. The system operates through a web portal that provides users with comparative information on HUMS parameters relative to fleet statistics. The user may view HUMS data for the entire fleet or drill down to a particular HUMS acquisition on a specific flight. The web based format also facilities display and communication of warnings in a timely manner.

摘要翻译： 卫生和使用监测系统（HUMS）利用一种通用架构，允许OEM和旋翼航空器运营商独立于飞机模型，HUMS供应商或原始数据格式来查看和趋势整个飞机机队的HUMS数据。 该系统通过门户网站进行操作，为用户提供有关HUMS参数相对于车队统计信息的比较信息。 用户可以查看整个车队的HUMS数据，或者查看特定航班上的特定HUMS采集。 基于网络的格式还可以及时显示和通知警告。

公开(公告)号：US5226350A

公开(公告)日：1993-07-13

申请号：US903066

申请日：1992-06-22

申请人： James P. Cycon ,  Vincent F. Millea ,  Fred W. Kohlhepp ,  Bruce D. Hansen

发明人： James P. Cycon ,  Vincent F. Millea ,  Fred W. Kohlhepp ,  Bruce D. Hansen

IPC分类号： B64C27/14 ,  B64C27/20 ,  F02B75/02 ,  F16D3/06 ,  F16D3/18

CPC分类号： B64C27/14 ,  B64C27/20 ,  F16D3/06 ,  F16D3/185 ,  F02B2075/025 ,  Y10T74/19074

摘要： A drive train assembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a sprag clutch, an engine coupling subassembly, a transmission coupling subassembly, and a drive shaft mechanically interconnected at the ends thereof to the engine and transmission coupling subassemblies, respectively. The drive train assembly is design optimized to maximize the functional capability of the sprag clutch, the engine coupling subassembly including an external crown spline coupling, internal spline coupling combination that is mounted in combination with the sprag clutch so that loads transmitted through the external crown spline coupling react through the center of the sprag clutch. Further, the drive train assembly is design optimized to maximize allowable axial, angular, and/or parallel misalignments between the engine and the rotor assembly as a result of the mechanical interconnection of the drive shaft to the external crown spline coupling, internal spline coupling combination of the engine coupling subassembly and to the external crown spline coupling, gear spline coupling combination of the transmission coupling subassembly. The drive shaft is configured as a torque tube having inside and outside diameters sized to provide torsionally soft drive shaft such that the drive shaft functions as a torsional spring to isolate spline coupling teeth, the sprag clutch, transmission gearing, and the rotor assembly from vibratory torque generated by the engine.

摘要翻译： 用于具有管道式同轴反向旋转转子的转子组件的传动系组件包括分离离合器，发动机联接子组件，变速器联轴器组件和在其端部机械相互连接到发动机和变速器联轴器组件的驱动轴 。 传动系组件被设计优化，以最大限度地发挥起落架离合器的功能能力，发动机联轴器组件包括外部花键联轴器，内部花键联接组合，与楔形离合器组合安装，使得通过外部冠状花键传递的载荷 联轴器通过楔形离合器的中心反作用。 此外，传动系组件被设计优化以使得由于驱动轴与外冠花键联轴器，内花键联接组合的机械互连而使发动机和转子组件之间的允许的轴向，角度和/或平行的不对准最大化 的发动机联轴器组件和外部花键联轴器，齿轮花键联轴器组合的变速器联轴器组件。 驱动轴被构造为具有内径和外径的扭矩管，扭矩管的尺寸设置成提供扭转软的驱动轴，使得驱动轴用作扭转弹簧以将花键联接齿，楔形离合器，传动齿轮传动装置和转子组件从振动 发动机产生的转矩。

公开(公告)号：US5048652A

公开(公告)日：1991-09-17

申请号：US440824

申请日：1989-11-24

申请人： James P. Cycon ,  Vincent F. Millea ,  Peter G. Sanders

发明人： James P. Cycon ,  Vincent F. Millea ,  Peter G. Sanders

IPC分类号： F16D11/10 ,  F16D43/14

CPC分类号： F16D43/14

摘要： A progressive clutch includes a centrifugal clutch 10 attached to a drive shaft and inserted into a clutch housing assembly 16 to engage with clutch material 28 during low rpm operation. As the rpm of the input drive shaft 2 increases, the centrifugal force on pellets 32 overcomes the force of compression springs 34, and extension springs 40 pull a pin engagement assembly 30 towards the clutch housing assembly 16 thus engaging pins 38 into elongated holes 42 to provide positive drive from the drive shaft 2 to the driven shaft 21.

公开(公告)号：US5340279A

公开(公告)日：1994-08-23

申请号：US903063

申请日：1992-06-22

申请人： James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

发明人： James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

IPC分类号： B64C27/10 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  B64C27/38

CPC分类号： B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

摘要： A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub. The snubber assembly includes a spherical self-aligning bearing, a bearing bolt, a locking nut, a snubber bracket secured in combination with the spherical bearing, and securing bolts. The spherical bearing, snubber bracket combination is rotatably mounted within the bearing cavity utilizing the bearing bolt. The bearing bolt is secured in combination with the rotor hub utilizing the locking nut, which is threaded onto the bearing bolt in the internal cavity to jam against the inboard internal bulkhead. The securing bolts are utilized to secure the snubber bracket in combination with the corresponding integrated torque tube/spar member of the rotor assembly.

摘要翻译： 一种用于转子组件的缓冲组件，其具有导管同轴的反向旋转转子，其设计优化以便于利用自对准轴承并安装在对应的挠性梁至转子轮毂附接接头的内侧，从而增强可接近性并减少维护 费用 转子组件的转子轮毂被设计为优化用于将缓冲器组件与其组合固定并且包括多个臂，每个臂形成用于将转子组件挠性束附接到转子毂的外侧U形夹。 在U形夹的内侧，每个转子轮毂臂包括具有穿过其中的螺栓孔的外侧内部隔板和具有穿过其中的螺栓孔的内侧内部隔板。 内侧和外侧的内部舱壁组合地限定了轴承腔和用于将缓冲器组件与转子毂组合固定的内部空腔。 缓冲组件包括球形自调心轴承，轴承螺栓，锁紧螺母，与球面轴承组合固定的缓冲支架和固定螺栓。 球轴承，缓冲支架组合使用轴承螺栓可旋转地安装在轴承腔内。 轴承螺栓利用锁定螺母与转子毂组合固定，该锁定螺母被拧到内部空腔中的轴承螺栓上以卡在内侧内部舱壁上。 紧固螺栓用于将缓冲支架与转子组件的相应的集成扭矩管/翼梁构件组合固定。

公开(公告)号：US4466774A

公开(公告)日：1984-08-21

申请号：US413029

申请日：1982-08-30

申请人： James P. Cycon ,  Timothy A. Krauss ,  Stephan Roman

发明人： James P. Cycon ,  Timothy A. Krauss ,  Stephan Roman

IPC分类号： B64C27/35 ,  B64C27/32 ,  B64C27/33 ,  B64C27/48

CPC分类号： B64C27/33 ,  B64C27/32

摘要： A helicopter rotor system using composite flexbeams for connecting a rotor blade to the rotor hub, each flexbeam being of C-section and having a web section made up of 0.degree. and .+-.45.degree. plies and top and bottom flanges made up of low angle plies in the direction of their length with their ends being connected by an arc of plies so that the top and bottom flange plies are continuous with an attachment fitting encased at the ends of the flexbeams.

摘要翻译： 一种直升机转子系统，使用复合柔性梁将转子叶片连接到转子轮毂上，每个柔性梁为C形截面，并具有由0°和+/- 45°层组成的腹板部分，顶部和底部凸缘由低 角度在它们的长度方向上，其端部通过一层叠层连接，使得顶部和底部凸缘层与包围在柔性梁的端部的附接配件连续。

公开(公告)号：US06170778B2

公开(公告)日：2001-01-09

申请号：US09296716

申请日：1999-04-22

申请人： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

发明人： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC分类号： B64C2730

CPC分类号： B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

摘要： A method for reducing a nose-up pitching moment in an unmanned aerial vehicle during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies that are mounted within a duct. Each rotor assembly includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor assemblies to produce a virtual plane across the duct. The virtual plane is operative for substantially deflecting air passing over the fuselage away from the duct. In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct to inhibit air that is flowing across the bottom of the duct from passing into the duct.

摘要翻译： 一种用于在远程飞行期间减少无人驾驶飞行器中的起搏俯仰力矩的方法。 无人驾驶飞行器包括安装在管道内的反向旋转转子组件。 每个转子组件包括多个转子叶片。 该方法包括调整转子叶片以使其基本上为零。 然后旋转转子组件以在管道上产生虚拟平面。 虚拟平面可操作用于使穿过机身的空气基本上偏转远离管道。 在本发明的一个实施例中，该方法包括阻碍管道底部的至少一部分的进一步的步骤，以阻止流过管道底部的空气进入管道。

公开(公告)号：US5575438A

公开(公告)日：1996-11-19

申请号：US239645

申请日：1994-05-09

申请人： Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

发明人： Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

IPC分类号： B64C27/10 ,  B64C27/20 ,  B64C39/02 ,  B64D47/00 ,  B64D47/08

CPC分类号： B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

摘要： An unmanned aerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem to facilitate landing of the VTOL UAV at unprepared ground surveillance sites.

摘要翻译： 无人飞行器（UAV）具有环形机身和转子组件，其具有与环形机身固定的同轴组合的一对反向旋转转子，以为无人机提供垂直起飞和着陆（VTOL）能力。 VTOL UAV的一个实施例通过包括外部安装的远程可控的可收缩传感器子系统特别地配置用于地面监视任务，其提供方位扫描能力和预定的仰角/凹陷扫描能力以完成地面监视任务和可折叠着陆 齿轮子系统，以便于在未准备的地面监视场所着陆无人机。

公开(公告)号：US5277380A

公开(公告)日：1994-01-11

申请号：US903060

申请日：1992-06-22

申请人： James P. Cycon ,  Kenneth M. Furnes ,  Fred W. Kohlhepp ,  Marvin D. Farrell ,  David F. Sandy

发明人： James P. Cycon ,  Kenneth M. Furnes ,  Fred W. Kohlhepp ,  Marvin D. Farrell ,  David F. Sandy

IPC分类号： B64C1/00 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06

CPC分类号： B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

摘要： An unmanned aerial vehicle having a toroidal fuselage structure that surrounds a pair of coaxial, multi-bladed, counter-rotating rotors. The toroidal fuselage structure is optimized to provide a highly efficient structure for reacting aerodynamic flight loads and rotor thrust loads of the UAV. The toroidal fuselage structure is further optimized to provide weight efficiency for minimizing power requirements.

摘要翻译： 一种具有环形机身结构的无人驾驶飞行器，其环绕一对同轴，多叶片，反向旋转的转子。 优化了环形机身结构，为空中动力学飞行载荷和无人机的转子推力载荷提供了高效的结构。 环形机身结构进一步优化，以提供重量效率以最小化功率需求。

公开(公告)号：US06270038B1

公开(公告)日：2001-08-07

申请号：US09296624

申请日：1999-04-22

申请人： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

发明人： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC分类号： B64C2900

CPC分类号： B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

摘要： An unmanned aerial vehicle that includes a fuselage with a partial toroidal forward portion, and an aft portion. A duct is formed through the fuselage and extends from the top to the bottom of the fuselage. Two counter-rotating rotor assemblies are mounted within the duct for providing downward thrust through the duct. The rotor assemblies are supported by a plurality of support struts. At least one engine is mounted within the fuselage and engages with the rotor assemblies. A pusher prop assembly is mounted to the aft portion of the fuselage. The pusher prop assembly is designed to provide forward thrust along the longitudinal axis of the aircraft. The pusher prop assembly includes a drive shaft that is engaged with the engine. A plurality of propellers are attached to and rotated by the drive shaft. A shroud is mounted to the aft portion of the fuselage around the propellers and is operative for channeling the air passing through the propellers in a substantially aft direction. A pair of wings is removably attached to the sides of the fuselage. Each wing preferably includes a fixed portion and a pivotal flaperon portion hinged to the fixed portion. Directional vanes are preferably mounted to the shroud downstream from the propellers and control flow out of the shroud. Deflectors may be mounted to the bottom of the fuselage across a portion of the duct to control flow of air into the duct.

摘要翻译： 一种包括具有部分环形前部的机身的无人飞行器和后部。 通过机身形成管道，并从机身的顶部延伸至底部。 两个反向旋转的转子组件安装在管道内，以提供通过管道的向下推力。 转子组件由多个支撑支柱支撑。 至少一个发动机安装在机身内并与转子组件接合。 推进支架组件安装在机身的后部。 推进支架组件被设计成沿着飞行器的纵向轴线提供向前的推力。 推进器组件包括与发动机接合的驱动轴。 多个螺旋桨附接到驱动轴并由驱动轴旋转。 护罩安装在机身周围的螺旋桨的后部，并且可操作用于沿基本向后的方向引导通过螺旋桨的空气。 一对机翼可拆卸地连接到机身侧面。 每个翼优选地包括固定部分和铰接到固定部分的枢转襟副翼部分。 定向叶片优选地安装到螺旋桨下游的护罩并且控制流出护罩。 导向器可以穿过管道的一部分安装到机身的底部，以控制进入管道的空气流。