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1. 发明授权

US09199720B2 Non-rotating stationary ground tube for a wind fairing 有权
标题翻译：用于风整流罩的非旋转静止地面管
公开(公告)号：US09199720B2
公开(公告)日：2015-12-01
申请号：US13222398
申请日：2011-08-31
申请人： Michael C. Lonergan , Fred W. Kohlhepp , Robert D. Beatty
发明人： Michael C. Lonergan , Fred W. Kohlhepp , Robert D. Beatty
IPC分类号： B64C7/00 , B64C27/10
CPC分类号： B64C7/00 , B64C27/10
摘要： A stationary ground tube for use in an aircraft rotor fairing includes a first cylindrical portion including a first bore aligned along a longitudinal axis, the cylindrical body portion having a tubular body from a first end to a second end; and a second cylindrical portion coupled to the first cylindrical portion, the second cylindrical portion including a second bore aligned along the longitudinal axis. The second cylindrical portion is coupled to the aircraft rotor fairing via at least one attachment device.
摘要翻译：用于飞机转子整流罩的固定地面管包括第一圆柱形部分，其包括沿着纵向轴线对准的第一孔，所述圆柱形主体部分具有从第一端到第二端的管状体; 以及联接到所述第一圆柱形部分的第二圆柱形部分，所述第二圆柱形部分包括沿着所述纵向轴线对准的第二孔。第二圆柱形部分经由至少一个附接装置联接到飞行器转子整流罩。

2. 发明授权

US5226350A Drive train assembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
标题翻译：用于转子组件的传动系组件，其具有导管的同轴反转转子
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。

3. 发明授权

US06295006B1 Flap angle measurement system for an active rotor control system 有权
标题翻译：主动转子控制系统的瓣瓣测量系统
公开(公告)号：US06295006B1
公开(公告)日：2001-09-25
申请号：US09293628
申请日：1999-04-16
申请人： Fred W. Kohlhepp
发明人： Fred W. Kohlhepp
IPC分类号： G08B2100
CPC分类号： B64C27/001 , B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： A flap angle measurement system is disclosed for a helicopter rotor blade. The blade includes a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap angle measurement system includes a Hall effect sensor mounted to the trailing edge of the rotor blade. The Hall effect sensor has a sensing face. A magnet is mounted to the flap at a location spaced apart from the pivot axis. The magnet has a pole axis that is located parallel to the sensing face of the Hall effect sensor. A power source supplies power to the Hall effect sensor. A controller receives output signals from the Hall effect sensor which are indicative of the location of the magnet with respect to the sensing face of the Hall effect sensor. The position of the flap relative to the trailing edge is determined based on the received signals from the Hall effect sensor. In one embodiment of the invention, there is a second Hall effect sensor mounted on the other end of the flap. The sensing face of the second Hall effect sensor points in a direction opposite from the sensing face of the first Hall effect sensor.
摘要翻译：公开了一种用于直升机转子叶片的翼片角度测量系统。叶片包括后缘和围绕枢转轴线铰接到后缘的至少一部分的翼片。折角测量系统包括安装在转子叶片后缘的霍尔效应传感器。霍尔效应传感器具有感测面。在与枢转轴线间隔开的位置处，磁体安装到翼片上。磁体具有平行于霍尔效应传感器的感测面的极轴。电源为霍尔效应传感器供电。控制器从霍尔效应传感器接收指示磁体相对于霍尔效应传感器的感测面的位置的输出信号。基于来自霍尔效应传感器的接收信号确定翼片相对于后缘的位置。在本发明的一个实施例中，存在安装在翼片另一端的第二霍尔效应传感器。第二霍尔效应传感器的感测面指向与第一霍尔效应传感器的感测面相反的方向。

4. 发明授权

US06196796B1 High torque actuation system for an active rotor control system 失效
标题翻译：用于主动转子控制系统的高扭矩驱动系统
公开(公告)号：US06196796B1
公开(公告)日：2001-03-06
申请号：US09296737
申请日：1999-04-22
申请人： Steven A. Lozyniak , Peter Frederick Lorber , Fred W. Kohlhepp , Lee A. Hoffman , Robert Morton , Richard B. Ferraro
发明人： Steven A. Lozyniak , Peter Frederick Lorber , Fred W. Kohlhepp , Lee A. Hoffman , Robert Morton , Richard B. Ferraro
IPC分类号： B64C900
CPC分类号： B64C27/615 , B64C2027/7272 , Y02T50/34
摘要： An actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex. The actuation system includes a fluid supply which is connected to first and second fluid supply lines. The fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator. The actuator includes a housing mounted within the rotor blade and having a channel formed in it. A butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes. A first port connects the first fluid supply line with two diametrically opposed lobes in the channel. A second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel. A torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap. The pressurization of the first fluid supply line causes the torque coupling to rotate in a first direction. The pressurization of the second supply fluid line causes the torque coupling to rotate in the opposite direction.
摘要翻译：一种致动系统，用于使直升机转子叶片上的翼片枢转，以减小叶片与前一叶片涡流的相互作用。致动系统包括连接到第一和第二流体供应管线的流体供应源。流体供应管线将加压流体从流体供给流向致动器。致动器包括安装在转子叶片内并具有形成在其中的通道的壳体。蝶形轴枢转地安装在通道内并具有横向延伸的臂，其将通道分成四个凸角。第一端口将第一流体供应管线与通道中的两个直径相对的叶片连接。第二端口将第二流体供应管线与通道中的另外两个直径相对的叶片连接。扭矩联轴器连接到蝶形轴并与翼片接合，使得扭矩联接器的旋转产生翼片的伴随旋转。第一流体供应管线的加压使得扭矩联接沿第一方向旋转。第二供给流体管路的加压使得扭矩联接沿相反方向旋转。

5. 发明申请

US20130052034A1 NON-ROTATING STATIONARY GROUND TUBE FOR A WIND FAIRING 有权
标题翻译：非旋转式静止式地面管用于风力发电
公开(公告)号：US20130052034A1
公开(公告)日：2013-02-28
申请号：US13222398
申请日：2011-08-31
申请人： Michael C. Lonergan , Fred W. Kohlhepp , Robert D. Beatty
发明人： Michael C. Lonergan , Fred W. Kohlhepp , Robert D. Beatty
IPC分类号： B64C7/00
CPC分类号： B64C7/00 , B64C27/10
摘要： A stationary ground tube for use in an aircraft rotor fairing includes a first cylindrical portion including a first bore aligned along a longitudinal axis, the cylindrical body portion having a tubular body from a first end to a second end; and a second cylindrical portion coupled to the first cylindrical portion, the second cylindrical portion including a second bore aligned along the longitudinal axis. The second cylindrical portion is coupled to the aircraft rotor fairing via at least one attachment device.
摘要翻译：用于飞机转子整流罩的固定地面管包括第一圆柱形部分，其包括沿着纵向轴线对准的第一孔，所述圆柱形主体部分具有从第一端到第二端的管状体; 以及联接到所述第一圆柱形部分的第二圆柱形部分，所述第二圆柱形部分包括沿着所述纵向轴线对准的第二孔。第二圆柱形部分经由至少一个附接装置联接到飞行器转子整流罩。

6. 发明授权

US5351913A Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
标题翻译：用于转子组件的同轴传动/中心毂子组件，其具有导管的，同轴的反向转动的转子
公开(公告)号：US5351913A
公开(公告)日：1994-10-04
申请号：US903065
申请日：1992-06-22
申请人： James P. Cycon , Fred W. Kohlhepp , Vincent F. Millea
发明人： James P. Cycon , Fred W. Kohlhepp , Vincent F. Millea
IPC分类号： B64C27/46 , B64C27/20 , B64C27/33 , B64C27/605 , B64C39/02 , F02B75/02 , B64D35/06
CPC分类号： B64C27/33 , B64C27/20 , B64C27/605 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025
摘要： One embodiment of a coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a single stage transmission, a transmission housing, and a center hub support structure that are structurally and functionally interactive. The transmission housing includes upper and lower standpipe housings secured in combination with a middle housing. The single stage transmission includes an input pinion gear rotatably mounted in combination with the middle housing, and upper and lower spiral bevel gears rotatably coupled in combination with the input pinion gear to provide counter-rotation thereof. The spiral bevel gears include integral rotor shafts, respectively, rotatably mounted in the standpipe housings. The hub support structure is configured for securement of the middle housing internally in combination therewith, with respective surfaces thereof in abutting engagement so that dynamic loads of the rotors and thermal loads are directly coupled into the hub support structure via the middle housing while bending moments of the rotors are canceled in the middle housing. The hub support structure has radially extending arms for mounting the coaxial transmission/center hub subassembly in fixed coaxial relation to an airframe structure and for coupling the dynamic and thermal loads to the airframe structure. External surfaces of the standpipe housings function as sliding surfaces for linear motion of swashplate subassemblies to minimize the separation between the rotors so that the airframe structure has a compact aerodynamic and structural envelope. The transmission housing is internally configured to provide a splash lubrication subsystem.
摘要翻译：具有导管的同轴反转转子的转子组件的同轴传动/中心毂子组件的一个实施例包括在结构和功能上相互作用的单级传动装置，变速器壳体和中心轮毂支撑结构。变速器壳体包括与中间壳体组合固定的上下立管壳体。单级变速器包括与中间壳体可旋转地安装的输入小齿轮，以及与输入小齿轮可旋转地联接以提供反向转动的上下螺旋锥齿轮。螺旋锥齿轮分别包括可旋转地安装在立管壳体中的整体转子轴。轮毂支撑结构构造成用于将中间壳体与内部固定在一起，其相应的表面相互接合，使得转子和热负载的动态载荷通过中间壳体直接联接到轮毂支撑结构中，同时弯曲力矩转子在中间房屋被取消。轮毂支撑结构具有径向延伸臂，用于将同轴传动/中心轮毂子组件安装成与机身结构固定的同轴关系，并将动态和热负载耦合到机体结构。立管外壳的外表面用作滑动表面，用于旋转斜盘组件的直线运动，以最小化转子之间的间隔，使机身结构具有紧凑的空气动力学和结构范围。变速器壳体内部配置为提供飞溅润滑子系统。

7. 发明授权

US06200096B1 Actuation system for an active rotor control system 失效
标题翻译：主动转子控制系统的启动系统
公开(公告)号：US06200096B1
公开(公告)日：2001-03-13
申请号：US09293428
申请日：1999-04-16
申请人： Fred W. Kohlhepp
发明人： Fred W. Kohlhepp
IPC分类号： B64C900
CPC分类号： B64C27/001 , B64C27/615 , B64C2027/7272 , Y02T50/34
摘要： A flap actuation system for a helicopter rotor blade. The rotor blade includes a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap actuation system includes at least one supply line mounted within the rotor blade and extending outward from the root end. The supply line is adapted to channel pressurized fluid. At least one actuator fluidly connected to the supply line. The actuator includes a displacement member and a head member. The head member is engaged with the flap and is adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the supply line. In one embodiment of the invention there are two supply lines, each extending outward from the root end and is adapted to channel pressurized fluid. There is at least one actuator fluidly connected to each supply line. The actuator on one of the supply lines is adapted to pivot the flap upward when pressurized, and the actuator on the other supply line is adapted to pivot the flap downward when pressurized.
摘要翻译：用于直升机转子叶片的翼片致动系统。转子叶片包括根部端部，尖端，后缘以及围绕枢转轴线铰接到后缘的至少一部分的翼片。翼片致动系统包括安装在转子叶片内并从根端向外延伸的至少一条供应线。供应管线适用于加压流体通道。至少一个致动器流体地连接到供应管线。致动器包括位移构件和头构件。头部构件与翼片接合并且当加压流体被输送通过供应管线时，适于使翼片围绕其枢轴枢转。在本发明的一个实施例中，存在两条供应管线，每条供应管线从根部向外延伸并适于通道加压流体。至少一个致动器流体地连接到每个供应管线。供电线路之一上的致动器适于在加压时向上枢转翼片，并且另一供应线路上的致动器适于在加压时将翼片向下枢转。

8. 发明授权

US5277380A Toroidal fuselage structure for unmanned aerial vehicles having ducted, coaxial, counter-rotating rotors 失效
标题翻译：具有管道，同轴，反向旋转转子的无人机的环形机身结构
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。

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