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1. 发明授权

US4583704A Pneumatic system structure for circulation control aircraft 失效
标题翻译：循环控制飞机气动系统结构
公开(公告)号：US4583704A
公开(公告)日：1986-04-22
申请号：US565433
申请日：1983-12-27
申请人： Timothy A. Krauss , Stephan Roman , Robert J. Beurer
发明人： Timothy A. Krauss , Stephan Roman , Robert J. Beurer
IPC分类号： B64C27/32 , B64C27/12
CPC分类号： B64C27/325
摘要： A plenum for a circulation control rotor aircraft which surrounds the rotor drive shaft (18) and is so constructed that the top (32), outer (38) and bottom (36) walls through compressed air is admitted are fixed to aircraft structure and the inner wall (34) through which air passes to rotor blades (14) rotates with the drive shaft and rotor blades.
摘要翻译：一种用于循环控制转子飞行器的增压室，其围绕转子驱动轴（18）并且被构造成通过压缩空气允许的顶部（32），外部（38）和底部（36）壁被固定到飞行器结构，并且空气通过转子叶片14的内壁（34）与驱动轴和转子叶片一起旋转。

2. 发明授权

US4466774A Composite flexbeam joint 失效
标题翻译：复合弹性接头
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。

3. 发明授权

US4297080A Rotor blade pitch control linkage 失效
标题翻译：转子叶片桨距控制联动
公开(公告)号：US4297080A
公开(公告)日：1981-10-27
申请号：US104605
申请日：1979-12-17
申请人： Timothy A. Krauss , Stephan Roman
发明人： Timothy A. Krauss , Stephan Roman
IPC分类号： B64C27/33 , B64C27/48 , B64C27/58 , B64C27/38
CPC分类号： B64C27/48 , B64C27/33 , B64C27/58
摘要： In a helicopter rotor, a blade control linkage is externally supported on the rotor hub and connected to the root end of a torque tube to provide torsion inputs to the blade by twisting the flexible spar member, which is enveloped by the torque tube and joined to the torque tube at a predetermined blade radial location. The linkage forms a parallelogram with the torque tube, and short vertical ball joint mounted links incline in two directions to accommodate blade lead/lag and flapping motions without introducing pitch coupling.
摘要翻译：在直升机转子中，叶片控制联动装置外部支撑在转子轮毂上并连接到扭矩管的根端，以通过扭转由扭矩管包围的柔性翼梁构件来向叶片提供扭转输入，并连接到扭矩管在预定的叶片径向位置。连杆与扭矩管形成平行四边形，并且短的垂直球形接头安装的连接件在两个方向上倾斜，以适应叶片前进/延迟和拍动运动，而不引入桨距联轴器。

4. 发明授权

US07252479B2 Rotor blade for a high speed rotary-wing aircraft 有权
标题翻译：用于高速旋翼飞机的转子叶片
公开(公告)号：US07252479B2
公开(公告)日：2007-08-07
申请号：US11140706
申请日：2005-05-31
申请人： Ashish Bagai , Robert C. Moffitt , Robert H. Blackwell, Jr. , Timothy A. Krauss
发明人： Ashish Bagai , Robert C. Moffitt , Robert H. Blackwell, Jr. , Timothy A. Krauss
IPC分类号： B64C27/46
CPC分类号： B64C27/10 , B64C27/467 , B64C27/82 , B64C2027/8236 , Y10S416/02 , Y10S416/05
摘要： A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil. Another characteristic feature of the rotor blade design is an unconventional combination of positive and negative twist gradients.
摘要翻译：具有独特平台形状的主转子叶片，其中叶片弦从叶片内侧区域的根部端延伸到叶片的外部主区域，其中叶片弦在主区域内的翼展方向位置处达到最大弦线，然后朝向远端尖端减小。前缘优选地大体上是直的，而后缘被轮廓化以限定弦。转子叶片设计的另一个特征是叶片羽化轴线的位置，其中羽化轴线位于转子叶片的一些内侧长度处的中间弦位置，然后转变到四分之一弦的位置。另一个特征是沿着叶片跨度的翼型分布，其从钝的后缘转变成适用于中档马赫数操作的锋利的后缘翼型。尖端区域优选地使用跨音速流动翼型件。转子叶片设计的另一个特征是正负扭转梯度的非常规组合。

5. 发明授权

US07695249B2 Bearingless rotor blade assembly for a high speed rotary-wing aircraft 有权
标题翻译：用于高速旋翼飞机的无轴转子叶片组件
公开(公告)号：US07695249B2
公开(公告)日：2010-04-13
申请号：US11565669
申请日：2006-12-01
申请人： Timothy A. Krauss , Pedro L. Cabrera , David H. Hunter
发明人： Timothy A. Krauss , Pedro L. Cabrera , David H. Hunter
IPC分类号： B64C27/32
CPC分类号： B64C27/10 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/50 , B64C27/58
摘要： A bearingless rotor system includes a flexbeam assembly having a first beam and a second beam arranged in a back-to-back orientation with a pitch shaft channeled therebetween. The beams morph into a rotor blade spar at an outboard rotor blade station. The outboard section of the flexbeam assembly receives the full pitch input from the pitch shaft while the most inboard section of the flexbeam assembly is essentially fixed in pitch by a blade attachment to a rotor hub assembly. The flexbeam assembly twist versus span is essentially linear from the most inboard to the most outboard rotor blade stations. The outboard rotor blade station, being attached to the outboard section of the flexbeam assembly, thereby also defines the pitch input equivalent from the outboard rotor blade station to the rotor blade tip.
摘要翻译：无轴承转子系统包括具有第一梁和第二梁的挠性束组件，所述第一梁和第二梁以背对背方向布置，其间具有间隙轴。梁在外侧转子叶片站处转变为转子叶片翼梁。柔性梁组件的外侧部分接收来自俯仰轴的全音高输入，而柔性梁组件的最内侧部分通过叶片附接到转子轮毂组件上的螺距基本固定。柔性梁组件扭转与跨度基本上是从内侧到最外侧的转子叶片站线性的。附接到柔性梁组件的外侧部分的外侧转子叶片工位从而还限定了从外侧转子叶片站到转子叶片尖端的等效输入。

6. 发明申请

US20080131280A1 BEARINGLESS ROTOR BLADE ASSEMBLY FOR A HIGH SPEED ROTARY-WING AIRCRAFT 有权
标题翻译：用于高速旋转飞行器的无轴承转子叶片组件
公开(公告)号：US20080131280A1
公开(公告)日：2008-06-05
申请号：US11565669
申请日：2006-12-01
申请人： Timothy A. Krauss , Pedro L. Cabrera , David H. Hunter
发明人： Timothy A. Krauss , Pedro L. Cabrera , David H. Hunter
IPC分类号： B64C27/37
CPC分类号： B64C27/10 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/50 , B64C27/58
摘要： A bearingless rotor system includes a flexbeam assembly having a first beam and a second beam arranged in a back-to-back orientation with a pitch shaft channeled therebetween. The beams morph into a rotor blade spar at an outboard rotor blade station. The outboard section of the flexbeam assembly receives the full pitch input from the pitch shaft while the most inboard section of the flexbeam assembly is essentially fixed in pitch by a blade attachment to a rotor hub assembly. The flexbeam assembly twist versus span is essentially linear from the most inboard to the most outboard rotor blade stations. The outboard rotor blade station, being attached to the outboard section of the flexbeam assembly, thereby also defines the pitch input equivalent from the outboard rotor blade station to the rotor blade tip.
摘要翻译：无轴承转子系统包括具有第一梁和第二梁的挠性束组件，所述第一梁和第二梁以背对背方向布置，其间具有间隙轴。梁在外侧转子叶片站处转变为转子叶片翼梁。柔性梁组件的外侧部分接收来自俯仰轴的全音高输入，而柔性梁组件的最内侧部分通过叶片附接到转子轮毂组件上的螺距基本固定。柔性梁组件扭转与跨度基本上是从内侧到最外侧的转子叶片站线性的。附接到柔性梁组件的外侧部分的外侧转子叶片工位从而还限定了从外侧转子叶片站到转子叶片尖端的等效输入。

7. 发明授权

US5340279A Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
标题翻译：用于转子组件的缓冲组件，其具有导管的同轴反转转子
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。

8. 发明授权

US5281099A Integrated spline/cone seat subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
标题翻译：用于转子组件的集成花键/锥座组件，具有导管同轴的反转转子
公开(公告)号：US5281099A
公开(公告)日：1994-01-25
申请号：US903064
申请日：1992-06-22
申请人： David H. Hunter , Timothy A. Krauss , Vincent F. Millea
发明人： David H. Hunter , Timothy A. Krauss , Vincent F. Millea
IPC分类号： B64C11/02 , B64C27/20 , B64C27/33 , B64C27/605 , B64C39/02 , F02B75/02
CPC分类号： B64C39/024 , B64C27/20 , B64C27/33 , B64C27/605 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025 , Y10T403/7035
摘要： An integrated spline/cone seat subassembly for a rotor assembly that is design optimized to minimize the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies thereof. The integrated subassembly includes a rotor hub having a shaft aperture with a plurality of hub splines extend radially inwardly therefrom. The lower portion of each hub spline has an outwardly tapered portion that makes a predetermined angle with respect to the hub centerline. The integrated subassembly further includes a rotor shaft having a primary shaft portion of a first diameter, an end shaft portion having an intermediate second diameter less than the first diameter, and a conic transition portion that makes a predetermined angle with respect to the rotor shaft axis. The end shaft portion has a plurality of shaft splines extending radially outwardly therefrom that defines a third diameter that is equal to the first diameter. The hub and shaft splines are sized to accommodate the torque required by the rotor assembly and interleaved to provide a rotational interlock between the rotor hub and rotor shaft. The tapered portions of the hub splines abuttingly engage and are mechanically supported by the conic transition portion of the rotor shaft. The first diameter of the rotor shaft defines the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies of the rotor assembly.
摘要翻译：用于转子组件的集成花键/锥座组件，其设计优化以使转子轴，转子轴轴承，变速器壳体和其斜盘组件的径向尺寸最小化。集成子组件包括具有轴孔的转子轮毂，其具有从其径向向内延伸的多个轮毂花键。每个毂花键的下部具有相对于轮毂中心线形成预定角度的向外的锥形部分。集成子组件还包括具有第一直径的主轴部分的转子轴，具有小于第一直径的中间第二直径的端轴部分和相对于转子轴轴线形成预定角度的圆锥过渡部分。端轴部分具有从其径向向外延伸的多个轴花键，其限定等于第一直径的第三直径。轮毂和轴花键的尺寸适于容纳转子组件所需的扭矩并交错以在转子毂和转子轴之间提供旋转互锁。轮毂花键的锥形部分邻接地接合并由转子轴的锥形过渡部分机械地支撑。转子轴的第一直径限定了转子轴，转子轴承，变速器壳体和转子组件的斜盘组件的径向尺寸。

9. 发明授权

US4028003A Torsionally compliant helicopter rotor blade with improved stability and performance characteristics 失效
标题翻译：扭转适应的直升机转子叶片，具有改进的稳定性和性能特性
公开(公告)号：US4028003A
公开(公告)日：1977-06-07
申请号：US675664
申请日：1976-04-12
申请人： Timothy A. Krauss
发明人： Timothy A. Krauss
IPC分类号： B64C27/46 , B64C27/467 , B64C27/44
CPC分类号： B64C27/46 , Y10S416/02
摘要： A torsionally compliant helicopter rotor blade with maximum blade torsional flexibility at the blade tip portion and so shaped at the blade root portion that the locus of shear centers and the locus of centers of lift are substantially coincident, and so shaped at the tip portion so that the locus of shear centers is selectively forward of the locus of centers of lift to establish an aerodynamic restoring moment in response to blade tip torsional excursions, thereby improving blade torsional stability.
摘要翻译：一种扭转兼容的直升机转子叶片，其在叶片尖端部分处具有最大的叶片扭转柔性，并且在叶片根部处成形，使得剪切中心的轨迹和提升中心的轨迹基本上重合，并且在尖端部分成形，使得剪切中心的位置选择性地在提升中心的轨迹前方，以响应于叶片尖端扭转偏移而建立空气动力学恢复力矩，从而提高叶片的扭转稳定性。

10. 发明授权

US5562416A Helicopter rotor blade mounting assembly 失效
公开(公告)号：US5562416A
公开(公告)日：1996-10-08
申请号：US512689
申请日：1995-08-10
申请人： David N. Schmaling , Frederick J. Knapp, Jr. , Timothy A. Krauss
发明人： David N. Schmaling , Frederick J. Knapp, Jr. , Timothy A. Krauss
IPC分类号： B64C27/48 , B64C27/38
CPC分类号： B64C27/48
摘要： A mounting assembly (50) for mechanically interconnecting a helicopter rotor blade (12) to a rotor hub assembly (10) and for mechanically interconnecting the rotor blade (12) to a damper assembly (52) and a pitch control input assembly (54). The rotor hub assembly (10) includes a hub plate (16) having a hub plate aperture (22) for mounting a rotor assembly yoke (24). The rotor assembly yoke (24) includes upper and lower radially extending arms (28a, 28b) which are disposed above and below the hub plate (16) and which include a set of mounting apertures (29) formed through the proximal end thereof. The mounting assembly (50) includes upper and lower clevis arms (60a, 60b) formed at the root end (56) of the rotor blade (12), a horn/damper fitting (64) interposed between the upper and lower clevis arms (60a, 60b), and upper and lower spacer plates (90a, 90b) disposed between the clevis arms (60a, 60b) and the radially extending arms (28a, 28b) of the rotor assembly yoke (24). The horn/damper fitting (64) includes first and second end portions (66, 68) which are configured for mounting to the damper assembly (52) and the pitch control input assembly (54). First and second sets of aligned apertures (102, 112) are formed in the upper and lower clevis arms (60a, 60b), the horn/damper fitting (64), and the upper and lower spacer plates (90a, 90b) for accepting first and second fastening members (100, 110). The first fastening members (100) are disposed through the first set of aligned apertures (102) for mechanically coupling the clevis arms (60a, 60b), the horn/damper fitting (64), and the spacer plates (90a, 90b) in combination. The second fastening members (110) are disposed through the mounting apertures (29) of the rotor assembly yoke (24) and the second set of aligned apertures (112) for mechanically coupling the rotor assembly yoke (64) and the spacer plates (90a, 90b) in combination.

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