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1. 发明授权

US09555880B2 Flexbeam rotor 有权
标题翻译： Flexbeam转子
公开(公告)号：US09555880B2
公开(公告)日：2017-01-31
申请号：US13368795
申请日：2012-02-08
申请人： David H. Hunter , Ryan Thomas Casey , Francis Edward Byrnes
发明人： David H. Hunter , Ryan Thomas Casey , Francis Edward Byrnes
IPC分类号： B64C27/33 , B64C27/35
CPC分类号： B64C27/33
摘要： A rotor hub assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectable to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.
摘要翻译：用于直升机的转子轮毂组件包括可操作地连接到直升机的轴的转子轮毂。一个或多个弯曲梁延伸穿过转子毂，每个柔性梁的每个端部可操作地连接到转子叶片。一个或多个内部轴承位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。用于直升机的转子组件包括可操作地连接到直升机的轴的转子轮毂。延伸穿过转子轮毂和一个或多个内部轴承的一个或多个弯曲梁位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。多个转子叶片可操作地连接到一个或多个柔性梁的端部。

2. 发明申请

US20120201678A1 FLEXBEAM ROTOR 有权
标题翻译： FLEXBEAM转子
公开(公告)号：US20120201678A1
公开(公告)日：2012-08-09
申请号：US13368795
申请日：2012-02-08
申请人： David H. Hunter , Ryan Thomas Casey , Francis Edward Byrnes
发明人： David H. Hunter , Ryan Thomas Casey , Francis Edward Byrnes
IPC分类号： B64C11/12
CPC分类号： B64C27/33
摘要： A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.
摘要翻译：用于直升机的转子轮毂组件包括可操作地连接到直升机的轴的转子轮毂。一个或多个弯曲梁延伸穿过转子毂，每个柔性梁的每个端部可操作地连接到转子叶片。一个或多个内部轴承位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。用于直升机的转子组件包括可操作地连接到直升机的轴的转子毂。延伸穿过转子轮毂和一个或多个内部轴承的一个或多个弯曲梁位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。多个转子叶片可操作地连接到一个或多个柔性梁的端部。

3. 发明授权

US09051047B2 Flexbeam rotor attachment to rotor blade 有权
标题翻译： Flexbeam转子附接到转子叶片
公开(公告)号：US09051047B2
公开(公告)日：2015-06-09
申请号：US13674351
申请日：2012-11-12
申请人： Eric S. Parsons , Eric Lucien Nussenblatt , Justin Thomas , Ryan Thomas Casey , David H. Hunter
发明人： Eric S. Parsons , Eric Lucien Nussenblatt , Justin Thomas , Ryan Thomas Casey , David H. Hunter
IPC分类号： B64C27/00 , B64C27/473 , B64C27/04 , B64C27/33 , B64C27/48
CPC分类号： B64C27/473 , B64C27/04 , B64C27/33 , B64C27/48
摘要： A rotor blade assembly includes a flex-beam member and a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length. A rotor blade surrounds the flex beam member and extends from the torque tube to a blade tip. A connecting pin assembly secures the rotor blade and the torque tube at the flex-beam member. The connecting pin assembly includes a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade from a first rotor blade side and a second pin member located at a second rotor blade side. A clamping load between the first pin member and the second pin member secures the rotor blade and torque tube to the flex-beam member.
摘要翻译：转子叶片组件包括弯曲梁构件和围绕柔性梁构件并且沿着转子叶片组件长度部分地延伸的扭矩管。转子叶片围绕柔性梁构件并且从扭矩管延伸到叶片尖端。连接销组件将转子叶片和扭矩管固定在挠性梁构件上。连接销组件包括第一销构件，其具有第一轴，第一轴至少部分地通过转子叶片从第一转子叶片侧延伸到转子叶片组件中，第二销构件位于第二转子叶片侧。第一销构件和第二销构件之间的夹紧负载将转子叶片和扭矩管固定到挠性梁构件。

4. 发明申请

US20150014476A1 FLEXBEAM ROTOR ATTACHMENT TO ROTOR BLADE 有权
标题翻译： FLEXBEAM转子与转子叶片的连接
公开(公告)号：US20150014476A1
公开(公告)日：2015-01-15
申请号：US13674351
申请日：2012-11-12
申请人： Eric S. Parsons , Eric Lucien Nussenblatt , Justin Thomas , Ryan Thomas Casey , David H. Hunter
发明人： Eric S. Parsons , Eric Lucien Nussenblatt , Justin Thomas , Ryan Thomas Casey , David H. Hunter
IPC分类号： B64C27/473 , B64C27/04
CPC分类号： B64C27/473 , B64C27/04 , B64C27/33 , B64C27/48
摘要： A rotor blade assembly includes a flex-beam member and a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length. A rotor blade surrounds the flex beam member and extends from the torque tube to a blade tip. A connecting pin assembly secures the rotor blade and the torque tube at the flex-beam member. The connecting pin assembly includes a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade from a first rotor blade side and a second pin member located at a second rotor blade side. A clamping load between the first pin member and the second pin member secures the rotor blade and torque tube to the flex-beam member.
摘要翻译：转子叶片组件包括弯曲梁构件和围绕柔性梁构件并且沿着转子叶片组件长度部分地延伸的扭矩管。转子叶片围绕柔性梁构件并且从扭矩管延伸到叶片尖端。连接销组件将转子叶片和扭矩管固定在挠性梁构件上。连接销组件包括第一销构件，其具有第一轴，第一轴至少部分地通过转子叶片从第一转子叶片侧延伸到转子叶片组件中，第二销构件位于第二转子叶片侧。第一销构件和第二销构件之间的夹紧负载将转子叶片和扭矩管固定到挠性梁构件。

5. 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。

6. 发明授权

US5785497A Control rod mounting arrangement for helicopter swashplates 失效
标题翻译：直升机斜盘的控制杆安装布置
公开(公告)号：US5785497A
公开(公告)日：1998-07-28
申请号：US814373
申请日：1997-03-11
申请人： Kevin A. White , David H. Hunter , Robert J. Milne , Stephen V. Poulin , Robert J. Trembicki
发明人： Kevin A. White , David H. Hunter , Robert J. Milne , Stephen V. Poulin , Robert J. Trembicki
IPC分类号： B64C27/32 , B64C27/605
CPC分类号： B64C27/605 , B64C27/32 , Y10T403/32122 , Y10T403/32221
摘要： A mounting arrangement (60) for coupling a control rod (38) to a stationary swashplate member (32) of a helicopter swashplate assembly (30) wherein the mounting arrangement (60) is characterized by a specially configured stationary swashplate member (32) and a trunnion fitting (62) for mounting in combination therewith. More specifically, the stationary swashplate member (32) includes a horizontal web (74) disposed between an inner ring segment (72.sub.IR) and an outer ring segment (72.sub.OR), wherein the horizontal web (74) includes an aperture (78) and defines a mounting surface (74.sub.S). The trunnion fitting (62) includes a base (64) defining a mounting surface (64.sub.S) and a pair of mounting ears (66) having aligned apertures (66.sub.O). The mounting surface (64.sub.S) of the trunnion fitting (62) engages the mounting surface (74.sub.S) of the horizontal web (74) such that the mounting ears (66) are disposed through the aperture (78) of the horizontal web (74). The mounting arrangement (60) further includes a mounting device (80) for demountably affixing the trunnion fitting (62) in combination with the horizontal web (74) and a coupling device (84), disposed in combination with the aligned apertures (66.sub.O), for coupling the control rod (38) in combination with the trunnion fitting (62).
摘要翻译：一种用于将控制杆（38）联接到直升机旋转斜盘组件（30）的固定旋转斜盘（32）的安装装置（60），其中所述安装装置（60）的特征在于特制的固定斜盘构件（32）和用于与其组合安装的耳轴配件（62）。更具体地，固定斜盘构件（32）包括设置在内环段（72IR）和外环段（72OR）之间的水平腹板（74），其中水平腹板（74）包括孔（78）并限定安装表面（74S）。耳轴配件（62）包括限定安装表面（64S）的基座（64）和具有对准的孔（66O）的一对安装耳（66）。耳轴接头（62）的安装表面（64S）接合水平腹板（74）的安装表面（74S），使得安装耳（66）穿过水平腹板（74）的孔（78）。安装装置（60）还包括安装装置（80），用于将耳轴配件（62）与水平腹板（74）组合安装，以及与对准的孔（66O）组合设置的联接装置（84），用于将控制杆（38）与耳轴接头（62）组合连接。

7. 发明授权

US5364230A Rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
标题翻译：用于转子组件的转子叶片子组件具有导管的同轴的反向旋转转子
公开(公告)号：US5364230A
公开(公告)日：1994-11-15
申请号：US903061
申请日：1992-06-22
申请人： Timothy A. Krauss , David H. Hunter , Robert D. Beatty
发明人： Timothy A. Krauss , David H. Hunter , Robert D. Beatty
IPC分类号： B64C27/10 , B64C27/12 , B64C27/20 , B64C27/33 , B64C27/46 , B64C27/605 , B64C39/02 , F02B75/02
CPC分类号： B64C27/605 , B64C27/20 , B64C27/33 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025
摘要： A rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a flexbeam, an integrated torque tube/spar member, and an aerodynamic fairing or rotor blade. The flexbeam is a laminated composite structure that reacts centrifugal loads and a majority of the bending loads of the rotor assembly. The flexbeam has a spanwise predetermined linear twist so that the pretwisted flexbeam is unstrained during specified forward flight conditions. The integrated torque tube/spar member is formed as a continuous, filament wound tubular composite structure having high torsional and bending stiffness that provides a continuous torsional load path and facilitates load coupling between the rotor blade and the pretwisted flexbeam. The spar segment of the functions as the primary structural member of the rotor blade subassembly and, is operative to react all bending, torsional, shear, and centrifugal dynamic loads of the rotor assembly. The torque tube segment reacts all torsional loads and some of the bending loads of the rotor assembly. The rotor blade is fabricated from a high modulus composite material and has a high aerodynamic taper such that the tapered rotor blade has a low outboard mass, a high inboard stiffness, and a high chordwise frequency. The high chordwise frequency allows the rotor assembly to be operated over a weaker modal response zone. The tapered rotor blade includes a triangularly shaped trailing edge segment that is responsive to the aerodynamic pressures encountered during operation of the shrouded counter-rotating rotors.
摘要翻译：具有导管的同轴反转转子的转子组件的转子叶片子组件包括柔性梁，集成的扭矩管/翼梁构件和空气动力学整流罩或转子叶片。柔性梁是一种叠层复合结构，可使离心载荷和转子组件的大部分弯曲载荷反应。柔性梁具有翼展方向预定的线性扭曲，使得预弯曲的柔性梁在指定的向前飞行条件下是不受约束的。集成的扭矩管/翼梁构件形成为具有高扭转和弯曲刚度的连续的长丝缠绕管状复合结构，其提供连续的扭转载荷路径并且有助于转子叶片和预扭曲挠曲梁之间的负载耦合。作为转子叶片子组件的主要结构构件的功能的翼梁段，可操作以对转子组件的所有弯曲，扭转，剪切和离心动态载荷作出反应。扭矩管段对转子组件的所有扭转载荷和一些弯曲载荷作出反应。转子叶片由高模量复合材料制成并且具有高空气动力学锥度，使得锥形转子叶片具有低的外侧质量，高的内侧刚度和高的弦向频率。高弦弦频率允许转子组件在较弱的模态响应区域上运行。锥形转子叶片包括三角形的后缘段，其响应于在遮蔽的反向旋转转子的操作期间遇到的空气动力学压力。

8. 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。

9. 发明授权

US5645400A Composite cuff structure for helicopter rotors 失效
标题翻译：用于直升机转子的复合箍结构
公开(公告)号：US5645400A
公开(公告)日：1997-07-08
申请号：US617012
申请日：1996-03-18
申请人： David H. Hunter , Karl B. Scherer
发明人： David H. Hunter , Karl B. Scherer
IPC分类号： B64C27/48 , B64C27/33 , B64C27/37 , B64C27/35
CPC分类号： B64C27/33
摘要： A composite cuff structure (40) for mounting the root end (14e) of a rotor blade assembly (14) to the radial arms (24a, 24b) of a rotor assembly yoke (24) and for accommodating a twist disparity therebetween. The composite cuff structure (40) is generally tubular in shape and is fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix. The composite cuff structure (40), furthermore, includes a blade-receiving sleeve portion (42), a yoke mounting portion (44), spanwise fold portions (46) and sidelobe portions (48), which portions (42, 44, 46, 48) are structurally integrated to form a unitary body. The blade-receiving sleeve portion (42) is disposed in combination with the root end (14e) of the rotor blade assembly (14) and includes first and second blade mounting segments (42a, 42b), which define a rotor blade attachment plane P.sub.B. The yoke mounting portion (44) is disposed in combination with the radial arms (24a, 24b) of the rotor assembly yoke (24) and includes fore and aft pairs (44-1, 44-2) of first and second yoke mounting segments (44a, 44b) defining a yoke attachment plane P.sub.Y. The pairs (44-1, 44-2) of yoke mounting segments (44a, 44b) are, furthermore, disposed laterally of the blade mounting segments (42a, 42b). The spanwise fold portions (46) include first and second complementary curve segments (46a, 46b) for structurally interconnecting the blade and yoke mounting segments (42a, 42b, 44a, 44b) such that the rotor blade attachment plane P.sub.B forms an angle .theta. with respect to the yoke attachment plane P.sub.Y. The sidelobe portions (48) include fore and aft curved segments (48a, 48b) for structurally interconnecting the first and second yoke mounting segments (44a, 44b).
摘要翻译：一种用于将转子叶片组件（14）的根端（14e）安装到转子组件轭（24）的径向臂（24a，24b）并用于在其间容纳扭曲差异的复合箍套结构（40）。复合箍结构（40）通常为管状形状，并由具有设置在结合基质中的增强纤维（70）的复合材料制成。此外，复合箍带结构（40）包括叶片接收套筒部分（42），轭架安装部分（44），翼展折叠部分（46）和旁瓣部分（48），该部分（42,44,46 ，48）在结构上整合形成整体。刀片接收套筒部分（42）与转子叶片组件（14）的根部端部（14e）组合设置并且包括第一和第二叶片安装段（42a，42b），其限定了转子叶片连接平面PB 。轭安装部分（44）与转子组件轭（24）的径向臂（24a，24b）组合设置，并且包括第一和第二轭安装段的前和后对（44-1,44-2）（44a，44b）限定轭附接平面PY。此外，轭安装段（44a，44b）的对（44-1,44-2）还设置在叶片安装段（42a，42b）的侧面。翼展折叠部分（46）包括第一和第二互补曲线段（46a，46b），用于将叶片和轭安装段（42a，42b，44a，44b）结构地互连，使得转子叶片附接平面PB与相对于轭附接平面PY。旁瓣部分（48）包括用于在第一和第二轭安装段（44a，44b）上结构互连的前后弯曲段（48a，48b）。

10. 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。

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