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1. 发明授权

US6074126A Structural interlock for inhibiting relative rotation between mating elements 失效
标题翻译：用于抑制配合元件之间的相对旋转的结构互锁
公开(公告)号：US6074126A
公开(公告)日：2000-06-13
申请号：US953744
申请日：1997-10-17
申请人： David H. Hunter , Francis E. Byrnes , Kevin S. French
发明人： David H. Hunter , Francis E. Byrnes , Kevin S. French
IPC分类号： F16D1/076 , F16D1/00
CPC分类号： F16D1/076 , Y10T403/32221 , Y10T403/32918 , Y10T403/4966 , Y10T403/74
摘要： A structural interlock (40) for inhibiting relative rotation between mating elements (20, 42) characterized by a plurality of grooves (50) being formed in one of the mating elements, and a mechanism (60) for producing a nominal contact pressure on the contact area (A.sub.1 thru A.sub.8) between the mating element, which contact pressure elastically deforms the other of the mating elements into the grooves (50), and is less than the material yield strength of either of the mating elements. In the preferred embodiment, the grooves (50) are radially oriented and an applied compressive load produces a nominal contact pressure which is about 80% of the material yield strength.
摘要翻译：用于抑制配合元件（20,42）之间的相对旋转的结构互锁（40），其特征在于在一个所述配合元件中形成有多个槽（50），以及用于在所述配合元件（20）上产生标称接触压力的机构接触区域（A1至A8）之间的接合压力，该接触压力将另一个配合元件弹性变形成凹槽（50），并且小于任一个配合元件的材料屈服强度。在优选实施例中，凹槽（50）径向定向并且施加的压缩载荷产生约为材料屈服强度的约80％的标称接触压力。

2. 发明授权

US09169011B2 Rotor with blades including outer blade shell and inner structural member 有权
标题翻译：带刀片的转子，包括外刀片外壳和内部结构件
公开(公告)号：US09169011B2
公开(公告)日：2015-10-27
申请号：US13231600
申请日：2011-09-13
申请人： David H. Hunter , Ryan T. Casey , Francis E. Byrnes
发明人： David H. Hunter , Ryan T. Casey , Francis E. Byrnes
IPC分类号： B64C27/473 , B64C27/32 , B64C27/33 , B64C27/58
CPC分类号： B64C27/473 , B64C27/32 , B64C27/33 , B64C27/58
摘要： A rotor for use in an aircraft includes an inner hub; and a plurality of blades arranged around the inner hub, each of the plurality of blades comprising an inner structural member; an outer blade shell surrounding the inner structural member; and a centering block located at a base of the inner structural member proximal to the inner hub, wherein the centering block is located between a first lateral portion of the inner structural member and a second lateral portion of the inner structural member, wherein the centering block is further connected to the outer blade shell, and wherein the centering block allows the outer blade shell to rotate about an axis approximately corresponding to the inner structural member.
摘要翻译：用于飞行器的转子包括内毂; 以及围绕所述内轮毂布置的多个叶片，所述多个叶片中的每一个包括内部结构构件; 围绕所述内部结构构件的外部叶片壳; 以及定位块，位于内结构件的靠近内毂的基部处，其中定心块位于内结构构件的第一侧部和内结构构件的第二侧部之间，其中定心块进一步连接到外刀片壳体，并且其中定心块允许外刀片壳体围绕大致对应于内部结构构件的轴线旋转。

3. 发明授权

US5601408A Axisymmetric elastomeric bearing assembly for helicopter rotors 失效
标题翻译：用于直升机转子的轴对称弹性轴承组件
公开(公告)号：US5601408A
公开(公告)日：1997-02-11
申请号：US617458
申请日：1996-03-18
申请人： David H. Hunter , Francis E. Byrnes , Douglas E. Tritsch
发明人： David H. Hunter , Francis E. Byrnes , Douglas E. Tritsch
IPC分类号： B64C27/35
CPC分类号： B64C27/35
摘要： An axisymmetric elastomeric bearing assembly (30) for an articulated rotor hub assembly (10), which axisymmetric elastomeric bearing assembly (30) is disposed in combination with a rotor assembly yoke (24) and hub retention member (12) of the rotor hub assembly (10) and is operative for accommodating the multi-directional displacement of a rotor blade assembly (14) thereof. The axisymmetric elastomeric bearing assembly (30) includes a central bearing element (32) having a spherical bearing surface (32s) defining a bearing focal point (30f) and spherical elastomeric elements (34) bonded to the spherical bearing surface (32s) on opposing sides of the bearing focal point (30f). Each of the spherical elastomeric elements (34) have a plurality of alternating layers of elastomer and nonresilient shims (36, 38) which have a center of curvature which is coincident with the bearing focal point (30f) and disposed at increasing radii therefrom. Bearing endplates (40) are bonded to the spherical elastomeric elements (34) and are mounted in combination with the yoke (24) and hub retention member (12). In operation, the central bearing element (32) is rotationally self-positioning to effect load and motion sharing between the spherical elastomeric elements (34).
摘要翻译：用于铰接式转子轮毂组件（10）的轴对称弹性体轴承组件（30），该轴对称弹性体轴承组件（30）与转子组件轭架（24）和转子轮毂组件的轮毂保持构件（12）组合设置（10）并且可操作用于容纳其转子叶片组件（14）的多向位移。轴对称弹性体轴承组件（30）包括具有限定轴承焦点（30f）的球面轴承表面（32s）和与球面轴承表面（32s）相对的球形弹性体元件（34）的中心轴承元件（32）轴承焦点（30f）的两侧。每个球形弹性体元件（34）具有多个弹性体和非弹性垫片（36,38）的交替层，其具有与支承焦点（30f）重合并以其增加的半径设置的曲率中心。轴承端板（40）被结合到球形弹性体元件（34）上并与轭架（24）和轮毂保持构件（12）组合安装。在操作中，中心轴承元件（32）是旋转自定位的，以实现球形弹性元件（34）之间的载荷和运动共享。

4. 发明申请

US20130064674A1 ROTOR WITH BLADES INCLUDING OUTER BLADE SHELL AND INNER STRUCTURAL MEMBER 有权
标题翻译：带叶片的转子，包括外部叶片和内部结构构件
公开(公告)号：US20130064674A1
公开(公告)日：2013-03-14
申请号：US13231600
申请日：2011-09-13
申请人： David H. Hunter , Ryan T. Casey , Francis E. Byrnes
发明人： David H. Hunter , Ryan T. Casey , Francis E. Byrnes
IPC分类号： B64C27/473
CPC分类号： B64C27/473 , B64C27/32 , B64C27/33 , B64C27/58
摘要： A rotor for use in an aircraft includes an inner hub; and a plurality of blades arranged around the inner hub, each of the plurality of blades comprising an inner structural member; an outer blade shell surrounding the inner structural member; and a centering block located at a base of the inner structural member proximal to the inner hub, wherein the centering block is located between a first lateral portion of the inner structural member and a second lateral portion of the inner structural member, wherein the centering block is further connected to the outer blade shell, and wherein the centering block allows the outer blade shell to rotate about an axis approximately corresponding to the inner structural member.
摘要翻译：用于飞行器的转子包括内毂; 以及围绕所述内轮毂布置的多个叶片，所述多个叶片中的每一个包括内部结构构件; 围绕所述内部结构构件的外部叶片壳; 以及定位块，位于内结构件的靠近内毂的基部处，其中定心块位于内结构构件的第一侧部和内结构构件的第二侧部之间，其中定心块进一步连接到外刀片壳体，并且其中定心块允许外刀片壳体围绕大致对应于内部结构构件的轴线旋转。

5. 发明授权

US5690474A Optimized composite flexbeam for helicopter tail rotors 失效
标题翻译：用于直升机尾旋翼的优化复合柔性梁
公开(公告)号：US5690474A
公开(公告)日：1997-11-25
申请号：US683490
申请日：1996-07-18
申请人： Francis E. Byrnes , Francis D. Federici , David N. Schmaling
发明人： Francis E. Byrnes , Francis D. Federici , David N. Schmaling
IPC分类号： B64C27/33 , B64C27/82 , B64C27/38
CPC分类号： B64C27/82 , B64C27/33
摘要： An optimized composite flexbeam (10) having a pitch region (PR) which includes a core laminate (50) of unidirectional fiberglass material (U.sub.F), and face laminates (52) of unidirectional graphite material (U.sub.G) bonded to mating surfaces (50.sub.M) defined by the core laminate (50). The core laminate (50) and face laminates define an aspect ratio which is greater than or equal to 10 and define chamfered edge surfaces (54.sub.S). Each chamfered edge surface (54.sub.S) defines a critical acute angle .alpha. with respect to the flapwise bending neutral axis (X.sub.A) of the pitch region (PR) and defines a lateral edge (54.sub.E) disposed a vertical distance X from the flapwise bending neutral axis (X.sub.A). The critical acute angle .alpha. is between about 14 degrees to about 22 degrees and the vertical distance X is about 12.5% to about 37.5% of the pitch region thickness dimension (T.sub.PR). The optimized composite flexbeam (10) further includes an inboard transition region (ITR) having a first transition subregion (ITR-1) and a second transition subregion (ITR-2). The second transition subregion (ITR-2) defines a width conic and a critical width transition subregion (Cr.sub.wt). Furthermore, the first and second inboard transition regions (ITR-1, ITR-2) are composed of a combination of unidirectional and off-axis composite materials (U, O) wherein the off-axis composite material (O) defines a percentage %O of off-axis composite material (O) and wherein the percentage %O in the critical transition subregion (CR.sub.wt) is defined by an optimized curve (100).
摘要翻译：具有包括单向玻璃纤维材料（UF）的芯层叠体（50）的节距区域（PR）和与配合表面（50M））接合的单向石墨材料（UG）的面层压板（52）的优化的复合柔性梁（10）由芯层压板（50）限定。芯层压板（50）和表面层压板限定大于或等于10的纵横比，并限定倒角边缘表面（54S）。每个倒角边缘表面（54S）相对于间距区域（PR）的折翼中性轴线（XA）限定了临界锐角α，并且限定了一个横向边缘（54E），该侧边缘设置有与折翼弯曲中立轴线（XA）。临界锐角α在约14度至约22度之间，垂直距离X为节距区域厚度尺寸（TPR）的约12.5％至约37.5％。优化的复合柔性梁（10）还包括具有第一过渡区域（ITR-1）和第二过渡区域（ITR-2）的内侧过渡区域（ITR）。第二个转移次区域（ITR-2）定义宽度圆锥和临界宽度转换次区域（Crwt）。此外，第一和第二内侧过渡区域（ITR-1，ITR-2）由单向和离轴复合材料（U，O）的组合构成，其中离轴复合材料（O）定义百分比％ O的离轴复合材料（O），并且其中临界转移区域（CRwt）中的百分比％O由优化曲线（100）定义。

6. 发明授权

US5431538A Hybrid composite flexbeam for a helicopter bearingless main rotor assembly 失效
标题翻译：用于直升机无轴承主转子组件的混合复合柔性梁
公开(公告)号：US5431538A
公开(公告)日：1995-07-11
申请号：US087826
申请日：1993-07-01
申请人： David N. Schmaling , Francis E. Byrnes
发明人： David N. Schmaling , Francis E. Byrnes
IPC分类号： B64C27/35 , B29C70/20 , B64C27/33
CPC分类号： B64C27/33 , B29C70/202
摘要： A hybrid composite flexbeam for a soft inplane bearingless main rotor assembly has eight spanwise regions: a hub attachment region; a first tapered region; a second tapered region; an inboard transition region; a pitch region having a cruciform configuration; an outboard transition region; a tapered outboard transition region; and a main rotor blade, torque tube attachment region. The pitch region is formed from unidirectional fiberglass plies, a 50/50 admixture of unidirectional fiberglass and graphite plies, and unidirectional graphite plies, all of which extend from root to tip of the hybrid flexbeam. Unidirectional fiberglass and graphite plies of varying lengths are interleaved in the second inboard tapered region. Fiberglass and graphite cross plies of varying lengths are interleaved in the first inboard tapered region. Fiberglass and graphite cross plies and unidirectional fiberglass plies of varying length are interleaved in the outboard tapered region. The ends of the plies of varying length form distributed ply drop-off arrangements in the first and second inboard tapered regions and the outboard tapered regions. The distributed arrangement of ply endings cause kick loads in the hybrid flexbeam to be distributed across the ply buildups. Fiberglass edge caps having a U-shaped configuration may be disposed in combination with the leading and trailing edges of the hybrid flexbeam, starting at the limits of the pitch region and extending inboardly and outboardly therefrom, respectively.
摘要翻译：用于软内平面无轴承主转子组件的混合复合柔性梁具有八个翼展区域：轮毂附接区域; 第一锥形区域; 第二锥形区域; 内部过渡区域; 具有十字形构造的节距区域; 舷外过渡区域锥形外侧过渡区域; 和主转子叶片，扭矩管附接区域。沥青区域由单向玻璃纤维帘布层，单向玻璃纤维和石墨层的50/50混合物以及单向石墨层形成，所有单向玻璃纤维帘布层均从根部到混合柔性梁的顶端延伸。不同长度的单向玻璃纤维和石墨层在第二内锥形区域中交错。不同长度的玻璃纤维和石墨交叉层在第一内锥形区域交错。不同长度的玻璃纤维和石墨交叉层和单向玻璃纤维帘布层在外侧锥形区域交错。不同长度的层的端部在第一和第二内侧锥形区域和外侧锥形区域中形成分布的帘布层落下布置。层状结构的分布式布置导致混合柔性梁中的脚蹬负载分布在层叠体上。具有U形构造的玻璃纤维边缘帽可以与混合柔性束的前缘和后缘结合设置，从间距区域的极限开始并分别从内侧延伸出来。

7. 发明授权

US5523530A Elastomeric acoustic insulator 失效
标题翻译：弹性声隔离器
公开(公告)号：US5523530A
公开(公告)日：1996-06-04
申请号：US279530
申请日：1994-07-25
申请人： Francis E. Byrnes , Ralph D. Costanza , Charles Isabelle
发明人： Francis E. Byrnes , Ralph D. Costanza , Charles Isabelle
IPC分类号： B64C27/00 , F16F15/08 , F16F15/00
CPC分类号： B64C27/001 , F16F15/08
摘要： An acoustic isolator is incorporated between a noise generating device and a support structure, such as between a transmission housing and an airframe. The isolator has a first fitting which attaches to the noise generating device, and a second fitting which attaches to the support structure, with an acoustic attenuation member disposed therebetween. Preferably, a first elastomer member is disposed between a pair of vertical walls of the first and second fittings. Optionally, a second elastomer member is disposed between an upper surface of the supporting structure and a lower surface of the second fitting such that horizontal loads are reacted therethrough. Alternatively the first and second elastomers comprise a spherical elastomer member and a cylindrical elastomer member in the form of a spherical bearing. The acoustic isolator thus allows rigid attachment of the adjacent structures yet provides acoustic isolation of complex forces which would normally transmit noise through the structure, particularly those from the vertical, lateral and fore/aft directions. Utilizing the inventive acoustic isolator, noise transmission through the support structure can be substantially reduced.
摘要翻译：声学隔离器结合在噪声产生装置和支撑结构之间，例如在变速器壳体和机身之间。隔离器具有附接到噪声产生装置的第一配件和附接到支撑结构的第二配件，其间设置有声衰减构件。优选地，第一弹性体构件设置在第一和第二配件的一对垂直壁之间。可选地，第二弹性体构件设置在支撑结构的上表面和第二配件的下表面之间，使得水平负载通过其反作用。或者，第一和第二弹性体包括球形弹性体构件和呈球形轴承形式的圆柱形弹性体构件。因此，声隔离器允许相邻结构的刚性附接，但是提供通常通过结构传播噪声的复杂力的声学隔离，特别是来自垂直，横向和前/后方向的结构。利用本发明的声隔离器，可以显着地减少通过支撑结构的噪声传输。

8. 发明授权

US5083725A Elastomeric swashplate configuration for helicopters 失效
标题翻译：直升机的弹性斜盘配置
公开(公告)号：US5083725A
公开(公告)日：1992-01-28
申请号：US598469
申请日：1990-10-11
申请人： Francis E. Byrnes , Edward S. Hibyan , Albert T. Krauss
发明人： Francis E. Byrnes , Edward S. Hibyan , Albert T. Krauss
IPC分类号： B64C27/605
CPC分类号： B64C27/605
摘要： A swashplate configuration for helicopter which eliminates the need for scissors linkages through the use of a centering member capable of tilt and axial translation while driving torque to the rotating swashplate member through the use of elastomeric bearing assemblies each consisting of a first stack of flat laminates and a second stack of spherical laminates.
摘要翻译：一种用于直升机的斜盘配置，其通过使用能够倾斜和轴向平移的定心构件来消除对剪刀的连接，同时通过使用弹性体轴承组件驱动扭矩，所述弹性体轴承组件由第一叠平板和第二层球形层压板。

9. 发明授权

US06578793B2 Method and apparatus for fiber strap termination 有权
公开(公告)号：US06578793B2
公开(公告)日：2003-06-17
申请号：US09782338
申请日：2001-02-13
申请人： Francis E. Byrnes , William P. Fallon
发明人： Francis E. Byrnes , William P. Fallon
IPC分类号： B64C2748
CPC分类号： B64C27/473 , B64C11/28
摘要： A variable diameter rotor blade assembly includes a rotor hub with multiple rotor blades each having an outboard blade section telescopically mounted to an inboard blade section. A reeling assembly includes a strap drum that extends and retracts a strap attached to each of the outboard blade sections to selectively change the diameter of the rotor blade assembly. The strap includes a body portion extending toward the drum and a termination portion attached to each of the outboard blade sections. The termination portion is made from a rigid fiber reinforced composite that has a higher rigidity than the body portion. A transition region is formed between the body portion and the termination portion and is made from a flexible matrix-fiber composite that has a higher rigidity than the body portion and a lower rigidity than the rigid fiber reinforced composite. The body portion is formed from layers of spanwise fibers and the termination portion is formed from alternating layers of spanwise fibers and angled fibers resulting in the termination portion having a greater thickness than the body portion. The orientation of the fibers in addition to the rigid fiber composite material increases the overall strength of the termination portion.

10. 发明授权

US06318527B1 Inertial vibration isolator spring for helicopter 有权
标题翻译：直升机用惯性隔振弹簧
公开(公告)号：US06318527B1
公开(公告)日：2001-11-20
申请号：US09454922
申请日：1999-12-03
申请人： Francis E. Byrnes , David N. Schmaling
发明人： Francis E. Byrnes , David N. Schmaling
IPC分类号： F16F710
CPC分类号： F16F15/1428 , B64C27/001 , F16F2230/0052
摘要： A novel apparatus and method are provided to reduce the interlaminar shear loading in the retention area of composite springs used in a vibration isolator for use with a helicopter main rotor. The composite springs, which are made of a graphite laminate, are weakest when subject to inter-laminate shear. The shear forces are highest during bending and twisting about the longitudinal axis of the laminate composite. The invention consists of several techniques to minimize the inter-laminate shear. The first is the use of nylon mounting pads which are attached to the ends of the graphite laminate spring arm at the locations where mounting to the inner and outer hubs is to take place. In particular, it has been found that the nylon spacer must be recessed back from the perimeter edges of the graphite spring arm the same distance which is approximately equal to the width of the graphite spring arm. Next the location of the bolt holes in the spring arm must be critically located so as to avoid that portion of the spring arm which has the highest shear loading.
摘要翻译：提供了一种新颖的装置和方法，以减少在与直升机主转子一起使用的隔振器中使用的复合弹簧的保持区域中的层间剪切载荷。由石墨层压制成的复合弹簧在层间剪切作用下最弱。在围绕叠层复合材料的纵向轴线的弯曲和扭转过程中剪切力最高。本发明由减少层间剪切力的几种技术组成。第一种是使用尼龙安装垫，它们在安装到内部和外部毂的位置处附接到石墨层压弹簧臂的端部。特别地，已经发现，尼龙隔片必须从与石墨弹簧臂的宽度大致相同的距离从石墨弹簧臂的周边边缘向后凹进。接下来，弹簧臂上的螺栓孔的位置必须严格定位，以避免弹簧臂的具有最高剪切载荷的部分。

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