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    Yoke for helicopter rotor systems
    1.
    发明授权
    Yoke for helicopter rotor systems 失效
    直升机转子系统的轭

    公开(公告)号：US5358381A

    公开(公告)日：1994-10-25

    申请号：US34345

    申请日：1993-03-19

    申请人： Cecil E. Covington ,  Timothy K. Ledbetter ,  Ernest A. Powell ,  Madison K. Robinson ,  Ajay Sehgal ,  Patrick R. Tisdale

    发明人： Cecil E. Covington ,  Timothy K. Ledbetter ,  Ernest A. Powell ,  Madison K. Robinson ,  Ajay Sehgal ,  Patrick R. Tisdale

    IPC分类号： B29C70/86 ,  B64C27/33 ,  B64C27/38

    CPC分类号： B64C27/33 ,  B29C70/86 ,  B29K2105/101 ,  B29L2031/08

    摘要： An improved feathering flexure for a helicopter rotor system yoke includes, in transverse cross section, a relatively thin central web and six relatively thin flanges. Three flanges extend from each of the web's two edges, and the flanges lie in planes which are approximately radial relative to the neutral feathering axis of the feathering flexure. The feathering flexure is constructed of fiberglass material embedded in a polymer matrix. The web's fiberglass material in the web is bias material, that is, material whose glass fibers are oriented at plus or minus 45 degrees relative to the yoke's spanwise axis. In transverse cross section, each of the flanges includes two unidirectional belts disposed on either side of a bias pack. The glass fibers in the unidirectional belts are oriented parallel to the yoke's spanwise axis. The fiberglass material in the bias packs is bias material. Each flange's unidirectional belts taper inwardly toward its bias pack adjacent to web, thereby decreasing the thickness of the flange adjacent to the web. In addition, the portion of each flange adjacent to the web is configured to minimize torsional rigidity and shear stress resulting from twisting the feathering flexure.

    摘要翻译： 用于直升机转子系统轭的改进的羽化挠曲在横截面中包括相对薄的中心腹板和六个相对薄的凸缘。 三个凸缘从每个腹板的两个边缘延伸，并且凸缘位于相对于羽化挠曲件的中性羽化轴线大致径向的平面中。 羽化挠曲由嵌入聚合物基体中的玻璃纤维材料构成。 幅材中的纤维网玻璃纤维材料是偏压材料，即玻璃纤维相对于轭的翼展轴线以正或负45度取向的材料。 在横截面中，每个凸缘包括设置在偏置组件的任一侧上的两个单向皮带。 单向带中的玻璃纤维平行于轭的翼展轴定向。 偏置组件中的玻璃纤维材料是偏压材料。 每个凸缘的单向带向内逐渐朝着与卷材相邻的偏压组件向内逐渐变细，从而减小了与卷材相邻的凸缘的厚度。 另外，与腹板相邻的每个凸缘的部分被构造成使扭转刚度和由于弯曲挠曲而产生的剪切应力最小化。

    Rotor system vibration absorber
    2.
    发明授权
    Rotor system vibration absorber 失效
    转子系统减震器

    公开(公告)号：US5647726A

    公开(公告)日：1997-07-15

    申请号：US599562

    申请日：1996-02-15

    申请人： Ajay Sehgal ,  Cecil E. Covington ,  Mithat Yuce ,  Bryan W. Marshall

    发明人： Ajay Sehgal ,  Cecil E. Covington ,  Mithat Yuce ,  Bryan W. Marshall

    IPC分类号： B64C27/51 ,  B64C27/00 ,  F16F15/12 ,  F16F15/133 ,  B64C27/06

    CPC分类号： B64C27/001 ,  B64C2027/003 ,  Y10S416/50

    摘要： A vibration absorber having a mass member which when static is supported by in-plane springs spaced apart from a base plate, top plate and spring retaining structures. The mass member has a bumper surface for contacting a motion limiter in the base plate. The mass member, base plate and top plate can have a passageway through the axis. The vibration absorber can be tuned by proper selection of the springs, degree of precompression and the variation of the amount of mass by the addition or removal of mass tuning weights.

    摘要翻译： 一种振动吸收器，具有质量部件，当静止由与基板，顶板和弹簧保持结构间隔开的平面内弹簧支撑时。 质量构件具有用于接触基板中的运动限制器的保险杠表面。 质量构件，基板和顶板可以具有穿过轴线的通道。 振动吸收器可以通过弹簧的适当选择，预压缩程度和质量调整量的变化来调节。

    Dual trunnion hub-to-mast assembly
    5.
    发明授权
    Dual trunnion hub-to-mast assembly 有权
    双耳轴到桅杆组合

    公开(公告)号：US06439849B1

    公开(公告)日：2002-08-27

    申请号：US09848478

    申请日：2001-05-03

    申请人： Ajay Sehgal ,  Glenn Shimek

    发明人： Ajay Sehgal ,  Glenn Shimek

    IPC分类号： B64C2735

    CPC分类号： B64C27/35 ,  B64C27/82

    摘要： The present invention comprises an apparatus for mounting two or more tail rotor hubs to a tail rotor mast. The apparatus comprises a mast having an externally-splined inboard section shaped and sized to mate with an internal spline on an inboard trunnion. The inboard trunnion is mechanically fixed to the one or more outboard hubs via a torsionally-rigid connection. The outboard portion of the mast is designed to have reduced torsional stiffness, so that torque is transmitted to the outboard trunnions through the inboard trunnion rather than through the mast.

    摘要翻译： 本发明包括用于将两个或更多个尾部转子毂安装到尾部转子桅杆上的装置。 该装置包括具有外花键内侧部分的桅杆，其内部花键形状和尺寸适于与内侧耳轴上的内花键配合。 内侧耳轴通过扭转刚性连接机械地固定到一个或多个外侧毂。 桅杆的外侧部分被设计成具有减小的扭转刚度，使得扭矩通过内侧耳轴而不是通过桅杆传递到舷外耳轴。

    Multi-bladed tail rotor hub design for coriolis relief
    6.
    发明授权
    Multi-bladed tail rotor hub design for coriolis relief 有权
    用于科里奥利浮雕的多叶尾转子轮毂设计

    公开(公告)号：US06764280B2

    公开(公告)日：2004-07-20

    申请号：US10090359

    申请日：2002-03-04

    申请人： Ajay Sehgal ,  Cecil Covington ,  David Haynie ,  Joseph Zierer ,  Eric Boyle

    发明人： Ajay Sehgal ,  Cecil Covington ,  David Haynie ,  Joseph Zierer ,  Eric Boyle

    IPC分类号： B64C2735

    CPC分类号： B64C27/35 ,  B64C27/48 ,  B64C27/82

    摘要： A multi-bladed tail rotor assembly is disclosed that provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within the bore, and retention means for aligning and securing the bearing assembly within the bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.

    摘要翻译： 公开了一种多叶片尾转子组件，其提供更高的空气动力性能，具有10,000小时寿命的损伤容限设计，并且其需要通过使用复合材料和弹性体的低维护。 尾部转子轮毂组件包括两个堆叠的轭组件，其具有多叶片旋转转子，每个安装在单个驱动桅杆上。 每个轭组件包括具有穿过其中的横向孔的轭架，设置在孔内的轴承组件和用于使轴承组件对准并固定在孔内的保持装置。 每个轴承组件包括具有从耳轴本体部分向外延伸的耳轴臂的耳轴部分和围绕每个耳轴臂设置的弹性体轴承。 尾部转子组件利用复合扭曲带弯曲以适应与每个转子叶片成一体的总体俯仰控制。

    Helicopter main rotor blade balance weight retention assembly
    9.
    发明授权
    Helicopter main rotor blade balance weight retention assembly 有权
    直升机主转子叶片平衡重量保持组件

    公开(公告)号：US07097427B2

    公开(公告)日：2006-08-29

    申请号：US10483641

    申请日：2002-08-02

    申请人： Norman Kuhns ,  Ajay Sehgal ,  Ernest Powell

    发明人： Norman Kuhns ,  Ajay Sehgal ,  Ernest Powell

    IPC分类号： B64C27/51

    CPC分类号： B64C27/008 ,  B64C27/473 ,  Y10S416/50

    摘要： A helicopter main rotor blade balance weight retention system and assembly having a base plate (105), at least one support post (107) integral with the base plate and extending out perpendicularly from the base plate, a plurality of balance weights (109), a retaining nut plate (111), and one or more fastening bolts (113) for securing the balance weights to the base plate, and the base plate to the rotor blade. The balance weights (109) include apertures (117, 119) through which the support posts and the fastening bolts pass. The apertures through which the support posts pass are dimensioned such that the a snug fit is formed between the support posts and the balance weight; but the apertures through which the fastening bolts pass are dimensioned such that the threaded portions of the fastening bolts are not subjected to any shear loads from the balance weights due to the centrifugal force generated by the rotating rotor blades. The weight retention assembly is installed into pockets in the blade tip.

    摘要翻译： 一种直升机主转子叶片平衡重量保持系统和组件，具有基板（105），至少一个支撑柱（107），与所述基板成一体并从所述基板垂直延伸出多个平衡重（109）， 保持螺母板（111）和用于将平衡重固定到基板的一个或多个紧固螺栓（113），以及将基板固定到转子叶片上。 平衡重（109）包括支撑柱和紧固螺栓穿过的孔（117,119）。 支撑柱通过的孔的尺寸设计成使得在支撑柱和平衡重之间形成贴合配合; 但是紧固螺栓通过的孔的尺寸被设计成使得紧固螺栓的螺纹部分由于旋转的转子叶片产生的离心力而不会受到来自平衡重的任何剪切载荷的影响。 重量保持组件安装在刀片尖端的凹穴中。