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24 条记录 (耗时 0.024 秒)

    Mission adaptive rotor blade
    4.
    发明授权
    Mission adaptive rotor blade 有权
    任务自适应转子叶片

    公开(公告)号：US09505492B2

    公开(公告)日：2016-11-29

    申请号：US13403364

    申请日：2012-02-23

    申请人： Mark W. Scott

    发明人： Mark W. Scott

    IPC分类号： B64C27/46 ,  B64C27/615 ,  B64C27/32

    CPC分类号： B64C27/615 ,  B64C27/325 ,  B64C27/463 ,  Y02T50/34

    摘要： A rotor assembly for a rotary wing aircraft includes a plurality of rotor blades operably connected to a rotor shaft. Two or more active adaptive devices are located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A method of operating a rotor assembly of a rotary wing aircraft includes rotating a plurality of rotor blades about a rotor shaft. Two or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly.

    摘要翻译： 用于旋转翼飞行器的转子组件包括可操作地连接到转子轴的多个转子叶片。 两个或多个主动适应装置位于多个转子叶片的一个或多个转子叶片上。 一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。 操作旋转翼飞行器的转子组件的方法包括绕转子轴旋转多个转子叶片。 位于多个转子叶片中的一个或多个转子叶片上的两个或多个主动自适应装置被致动并改变转子组件的一个或多个操作特性。

    High speed compound rotary wing aircraft
    5.
    发明授权
    High speed compound rotary wing aircraft 有权
    高速复合旋翼飞机

    公开(公告)号：US09120567B2

    公开(公告)日：2015-09-01

    申请号：US13493559

    申请日：2012-06-11

    申请人： Mark W. Scott ,  Stephen M. Gatto

    发明人： Mark W. Scott ,  Stephen M. Gatto

    IPC分类号： B64C27/57 ,  B64C27/72 ,  B64C27/82 ,  B64C21/04 ,  B64C21/08

    CPC分类号： B64C27/72 ,  B64C21/04 ,  B64C21/08 ,  B64C27/82 ,  B64C2027/7227 ,  B64C2027/725 ,  B64C2027/7266 ,  B64C2027/8236 ,  B64C2230/06 ,  B64C2230/14 ,  B64C2230/20 ,  B64C2230/28 ,  Y02T50/166 ,  Y02T50/34

    摘要： A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending.

    摘要翻译： 旋转翼飞机包括从机身延伸的气翼和延伸尾翼。 主转子组件可操作地连接到机身并且包括可操作地连接到转子轴的多个转子叶片，以及位于多个转子叶片的一个或多个转子叶片处的一个或多个主动适应装置。 一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。 尾部转子可操作地连接到延伸尾部。 尾部转子可围绕尾部转子轴线旋转，并且尾部转子轴线可从横向延伸到向后延伸。

    MISSION ADAPTIVE ROTOR BLADE
    6.
    发明申请
    MISSION ADAPTIVE ROTOR BLADE 有权
    任务自适应转子叶片

    公开(公告)号：US20130224017A1

    公开(公告)日：2013-08-29

    申请号：US13403364

    申请日：2012-02-23

    申请人： Mark W. Scott

    发明人： Mark W. Scott

    IPC分类号： F01D5/02 ,  F01D5/00

    CPC分类号： B64C27/615 ,  B64C27/325 ,  B64C27/463 ,  Y02T50/34

    摘要： A rotor assembly for a rotary wing aircraft includes a plurality of rotor blades operably connected to a rotor shaft. Two or more active adaptive devices are located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A method of operating a rotor assembly of a rotary wing aircraft includes rotating a plurality of rotor blades about a rotor shaft. Two or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly.

    摘要翻译： 用于旋转翼飞行器的转子组件包括可操作地连接到转子轴的多个转子叶片。 两个或多个主动适应装置位于多个转子叶片的一个或多个转子叶片上。 一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。 操作旋转翼飞行器的转子组件的方法包括绕转子轴旋转多个转子叶片。 位于多个转子叶片中的一个或多个转子叶片上的两个或多个主动自适应装置被致动并改变转子组件的一个或多个操作特性。

    HIGH SPEED COMPOUND ROTARY WING AIRCRAFT
    9.
    发明申请
    HIGH SPEED COMPOUND ROTARY WING AIRCRAFT 有权
    高速化合物旋转翼飞机

    公开(公告)号：US20130327879A1

    公开(公告)日：2013-12-12

    申请号：US13493559

    申请日：2012-06-11

    申请人： Mark W. Scott ,  Stephen M. Gatto

    发明人： Mark W. Scott ,  Stephen M. Gatto

    IPC分类号： B64C27/72 ,  B64C27/82

    CPC分类号： B64C27/72 ,  B64C21/04 ,  B64C21/08 ,  B64C27/82 ,  B64C2027/7227 ,  B64C2027/725 ,  B64C2027/7266 ,  B64C2027/8236 ,  B64C2230/06 ,  B64C2230/14 ,  B64C2230/20 ,  B64C2230/28 ,  Y02T50/166 ,  Y02T50/34

    摘要： A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending.

    摘要翻译： 旋转翼飞机包括从机身延伸的气翼和延伸尾翼。 主转子组件可操作地连接到机身并且包括可操作地连接到转子轴的多个转子叶片，以及位于多个转子叶片的一个或多个转子叶片处的一个或多个主动适应装置。 一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。 尾部转子可操作地连接到延伸尾部。 尾部转子可围绕尾部转子轴线旋转，并且尾部转子轴线可从横向延伸到向后延伸。

    System and method for improved rotary-wing aircraft performance with interior/external loads
    10.
    发明授权
    System and method for improved rotary-wing aircraft performance with interior/external loads 有权
    改进旋翼飞机性能与内部/外部载荷的系统和方法

    公开(公告)号：US07954766B2

    公开(公告)日：2011-06-07

    申请号：US11455482

    申请日：2006-06-19

    申请人： Steven J. Brainard ,  David R. Houy ,  Anthony Z. Stobiecki ,  Mark W. Scott ,  Steven D. Weiner

    发明人： Steven J. Brainard ,  David R. Houy ,  Anthony Z. Stobiecki ,  Mark W. Scott ,  Steven D. Weiner

    IPC分类号： B64D47/00

    CPC分类号： B64D1/22 ,  G01D7/02 ,  G01M1/127 ,  G05D1/0858

    摘要： An interactive aircraft load management system automates calculation and provides simulation capability to changes in an aircraft C.G. limit for display on a three-dimensional aircraft symbology. The aircraft load management system also communicates with a fly by wire (FBW) flight control system wherein the aircraft's control system is programmed to automatically compensate for C.G. excursions and to alter control laws. The aircraft load management system also selectively reels-in and reels out sling lines as the aircraft pitches and rolls to maintain a load vector from a slung load along the aircraft centerline. Load vector travel is accomplished by coupling a winch control system into the flight control system.

    摘要翻译： 交互式飞机负载管理系统自动计算并提供对飞机C.G.的变化的模拟能力。 限制在三维飞机符号系统上显示。 飞机负载管理系统还与飞行（FBW）飞行控制系统进行通信，其中飞行器的控制系统被编程为自动补偿C.G. 游览和改变控制法。 航空器负载管理系统还可以选择性地卷起并卷起吊索，因为飞机的间距和滚动以沿着飞机中心线保持来自悬挂载荷的载荷矢量。 通过将绞盘控制系统连接到飞行控制系统来实现负载矢量行驶。