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1. 发明申请

US20110274550A1 Yoke and Bearing Fitting Assembly for Rotors 有权
标题翻译：转子的轭和轴承配件组件
公开(公告)号：US20110274550A1
公开(公告)日：2011-11-10
申请号：US13144510
申请日：2009-01-19
申请人： Frank B. Stamps , Patrick R. Tisdale , Thomas C. Campbell , Richard E. Rauber , James L. Braswell
发明人： Frank B. Stamps , Patrick R. Tisdale , Thomas C. Campbell , Richard E. Rauber , James L. Braswell
IPC分类号： B64C11/04
CPC分类号： B64C27/33 , B64C27/32
摘要： A yoke and bearing fitting assembly for a multi-blade aircraft rotor is disclosed. The assembly has a yoke having arms extending generally radially from a central portion of the yoke, the arms each having opposing surfaces. An aperture is formed in each arm and extends between the surfaces. A bearing fitting has a body configured for insertion into the aperture of the yoke and has two rims protruding from a periphery of the body, the body also having a bearing mount adapted for mounting a pitch change bearing assembly to the yoke. Each rim abuts one of the surfaces of the associated yoke arm when the bearing fitting is installed within the aperture, so as to create clamping forces between the rims and the arm and the arm. The bearing fitting transmits forces from the pitch bearing assembly into the yoke.
摘要翻译：公开了一种用于多叶片飞行器转子的轭和轴承配件组件。组件具有轭，其具有从轭的中心部分大致径向延伸的臂，每个臂具有相对的表面。在每个臂中形成一个孔，并在表面之间延伸。轴承配件具有构造成用于插入轭的孔中并具有从主体的周边突出的两个轮缘的主体，该主体还具有适于将变桨轴承组件安装到轭的轴承座。当轴承配件安装在孔内时，每个轮辋邻接相关联的轭臂的一个表面，以便在轮辋与臂和臂之间产生夹紧力。轴承配件将变桨轴承组件的力传递到轭架中。

2. 发明授权

US07665969B2 Assembly for providing flexure to blade system 有权
标题翻译：用于向刀片系统提供弯曲的组件
公开(公告)号：US07665969B2
公开(公告)日：2010-02-23
申请号：US11040173
申请日：2005-01-24
申请人： Frank B. Stamps , Patrick R. Tisdale , James L. Braswell , Charles L. Baskin, Jr. , Tom Campbell , Timothy K. Ledbetter , Joseph J. Zierer , D. J. Reddy , Mark A. Wiinikka , Ronnie L. Martin , David A. Haynie , Stanley Gene Sadler , Ron Measom , Paul Oldroyd , Tricia Hiros , Jim Harse , Bob Mullins
发明人： Frank B. Stamps , Patrick R. Tisdale , James L. Braswell , Charles L. Baskin, Jr. , Tom Campbell , Timothy K. Ledbetter , Joseph J. Zierer , D. J. Reddy , Mark A. Wiinikka , Ronnie L. Martin , David A. Haynie , Stanley Gene Sadler , Ron Measom , Paul Oldroyd , Tricia Hiros , Jim Harse , Bob Mullins
IPC分类号： B63H1/06
CPC分类号： B64C27/48 , B64C27/33
摘要： An assembly for providing flexure to a blade of a rotary blade system, the assembly including an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces having a layer of cushioning material positioned thereon and secured thereto. The layer of cushioning material extending along and following the general contour of yoke surface, and the layer of cushioning material directly contacting a support plate. Another embodiment is an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle.
摘要翻译：一种用于向旋转刀片系统的刀片提供弯曲的组件，该组件包括具有上曲面的上支撑板，具有下弯曲表面的下支撑板和位于其间的轭。上和下磁轭表面中的至少一个具有定位在其上并固定到其上的缓冲材料层。缓冲材料层沿着轭铁表面的一般轮廓延伸并且沿着磁体表面的一般轮廓延伸，并且缓冲材料层直接接触支撑板。另一个实施例是用于向旋转刀片系统的刀片提供弯曲的组件，包括具有上曲面的上支撑板，具有下弯曲表面的下支撑板和位于其间的直接接触支撑板其中一个弯曲表面是不形成圆周的一部分的非圆弧。

3. 发明申请

US20080247876A1 Soft In-Plane Tiltrotor Hub 有权
标题翻译：软平面倾斜轮毂
公开(公告)号：US20080247876A1
公开(公告)日：2008-10-09
申请号：US10567886
申请日：2004-08-27
申请人： Frank B. Stamps , Michael R. Smith , Christopher M. Bothwell , Lawrence M. Corso , James L. Braswell , David A. Popelka , Ernst C. Schellhase , Charles L Hollimon , Thomas J. Newman , Bryan Baskin , Thomas C. Campbell , Daniel B. Robertson
发明人： Frank B. Stamps , Michael R. Smith , Christopher M. Bothwell , Lawrence M. Corso , James L. Braswell , David A. Popelka , Ernst C. Schellhase , Charles L Hollimon , Thomas J. Newman , Bryan Baskin , Thomas C. Campbell , Daniel B. Robertson
IPC分类号： B64C27/37 , B64C27/51
CPC分类号： F16F13/08 , B64C27/35 , B64C27/39 , B64C27/51 , F16F13/24 , F16F13/26 , F16F2230/30
摘要： A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.
摘要翻译：用于旋转翼飞行器的转子轮毂组件具有中心构件和适于将转子叶片附接到中心构件的多个叶片把手。刀片夹具可枢转地附接到中心构件并且能够围绕大致垂直于叶片的旋转平面的枢转轴线枢转。枢转允许叶片相对于中心构件的面内运动。阻尼器可操作地连接到每个叶片夹持件，用于阻尼相关叶片的平面内运动，每个阻尼器可在至少两个弹簧刚度之间切换。

4. 发明授权

US08764396B2 Lead-lag damper for rotor hubs 有权
标题翻译：用于转子轮毂的牵引阻尼器
公开(公告)号：US08764396B2
公开(公告)日：2014-07-01
申请号：US12866920
申请日：2008-02-12
申请人： Frank B. Stamps , James L. Braswell , David A. Haynie , Mithat Yuce
发明人： Frank B. Stamps , James L. Braswell , David A. Haynie , Mithat Yuce
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , F16F13/08
摘要： A lead-lag damper for a rotor assembly has a body mounted to either an inboard portion of a blade assembly or a fixed portion of the rotor assembly. A piston carried within the body is configured to allow for relative motion between the body and the piston. The piston defines opposing chambers within the body, the chambers being in fluid communication through a fluid passage. A link connects the piston to the other of the inboard portion of the blade assembly and the fixed portion of the rotor assembly, and the link engages a central portion of the piston. The piston acts on fluid in the chambers during relative motion between the piston and the body and causes fluid flow between the chambers through the fluid passage. Flow through the passage acts to damp lead-lag motion of the blade assembly relative to the fixed portion of the rotor assembly.
摘要翻译：用于转子组件的超前滞后阻尼器具有安装到叶片组件的内侧部分或转子组件的固定部分的主体。承载在主体内的活塞构造成允许主体和活塞之间的相对运动。活塞在体内限定相对的腔室，腔室通过流体通道流体连通。连杆将活塞连接到叶片组件的内侧部分中的另一个和转子组件的固定部分，并且连杆接合活塞的中心部分。在活塞和主体之间的相对运动期间，活塞作用在腔室中的流体上，并且通过流体通道引起腔室之间的流体流动。通过通道的流动用于阻止叶片组件相对于转子组件的固定部分的牵引延迟运动。

5. 发明申请

US20110027083A1 Lead-Lag Damper for Rotor Hubs 有权
标题翻译：转子毂的牵引阻尼器
公开(公告)号：US20110027083A1
公开(公告)日：2011-02-03
申请号：US12866920
申请日：2008-02-12
申请人： Frank B. Stamps , James L. Braswell , David A. Haynie , Mithat Yuce
发明人： Frank B. Stamps , James L. Braswell , David A. Haynie , Mithat Yuce
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , F16F13/08
摘要： A lead-lag damper for a rotor assembly has a body mounted to either an inboard portion of a blade assembly or a fixed portion of the rotor assembly. A piston carried within the body is configured to allow for relative motion between the body and the piston. The piston defines opposing chambers within the body, the chambers being in fluid communication through a fluid passage. A link connects the piston to the other of the inboard portion of the blade assembly and the fixed portion of the rotor assembly, and the link engages a central portion of the piston. The piston acts on fluid in the chambers during relative motion between the piston and the body and causes fluid flow between the chambers through the fluid passage. Flow through the passage acts to damp lead-lag motion of the blade assembly relative to the fixed portion of the rotor assembly.
摘要翻译：用于转子组件的超前滞后阻尼器具有安装到叶片组件的内侧部分或转子组件的固定部分的主体。承载在主体内的活塞构造成允许主体和活塞之间的相对运动。活塞在体内限定相对的腔室，腔室通过流体通道流体连通。连杆将活塞连接到叶片组件的内侧部分中的另一个和转子组件的固定部分，并且连杆接合活塞的中心部分。在活塞和主体之间的相对运动期间，活塞作用在腔室中的流体上，并且通过流体通道引起腔室之间的流体流动。通过通道的流动用于阻止叶片组件相对于转子组件的固定部分的牵引延迟运动。

6. 发明授权

US07957851B2 System and method for utilization of transmitted digital flight data acquisition information to accomplish vibration balance solutions 有权
标题翻译：用于传输数字飞行数据采集信息的系统和方法，以实现振动平衡解决方案
公开(公告)号：US07957851B2
公开(公告)日：2011-06-07
申请号：US11124759
申请日：2005-05-09
申请人： James L. Braswell , Daniel Craycraft
发明人： James L. Braswell , Daniel Craycraft
IPC分类号： G06F17/00
CPC分类号： F01D5/10 , F01D5/027 , F01D17/20 , F05D2260/96 , F05D2270/114 , Y02T50/671
摘要： A system and method is provided for monitoring, collecting, storing, transmitting, calculating and uploading to a secure web server real-time balancing solutions for at least the N1 Low Pressure Compressor portion of a jet engine. The method comprises collecting a series of engine vibration data strings and transmitting a data string set to a ground stations for conditioning, formatting and forwarding to a source for calculating and providing fan balance solutions to a secure server wherein the data strings comprise at least phase angle of imbalance data, N1 RPM and the magnitude of the N1 vibration. The balance solution determined comprises the required weight (mass) and location of weight (mass) installation necessary to correct a fan imbalance in a turbine engine.
摘要翻译：提供了一种系统和方法，用于监控，收集，存储，传输，计算和上传到安全的Web服务器，实时平衡至少是喷气发动机的N1低压压缩机部分的解决方案。该方法包括收集一系列发动机振动数据串，并将设置到地面站的数据串发送到地面站，用于调节，格式化和转发到源，以计算并向安全服务器提供风扇平衡解决方案，其中数据串至少包括相位角的不平衡数据，N1 RPM和N1振幅的大小。确定的平衡溶液包括校正涡轮发动机中的风扇不平衡所需的重量（质量）和重量（质量）安装所需的位置。

7. 发明授权

US4120610A Helicopter blade structure 失效
标题翻译：直升机叶片结构
公开(公告)号：US4120610A
公开(公告)日：1978-10-17
申请号：US470520
申请日：1974-05-16
申请人： James L. Braswell , Cecil E. Covington , Nolan B. Phillips , David E. Snyder
发明人： James L. Braswell , Cecil E. Covington , Nolan B. Phillips , David E. Snyder
IPC分类号： B64C27/46 , B64C27/473 , B64C27/48
CPC分类号： B64C27/473 , B64C2027/4736
摘要： A helicopter main rotor blade having a metallic nose spar extending the length of the leading edge of the blade and a trailing edge skin attached to the nose spar. A closure channel fixed within the nose spar extends the length thereof with unidirectional fiberglass material fixed to and extending along the length of the closure channel. A bushing on the inboard end of the blade preferably is attached both to the nose spar and the fiberglass bands for transfer of centrifugal forces in the blade to a grip.
摘要翻译：具有延伸叶片前缘长度的金属鼻梁的直升机主转子叶片和附着在鼻梁上的后缘皮肤。固定在鼻翼梁内的封闭通道用固定在封闭通道的长度上并沿其延伸的单向玻璃纤维材料延伸长度。叶片内侧端的衬套优选地连接到鼻梁和玻璃纤维带上，用于将叶片中的离心力转移到手柄。

8. 发明授权

US4083656A Composite rotor blade 失效
标题翻译：复合转子叶片
公开(公告)号：US4083656A
公开(公告)日：1978-04-11
申请号：US560587
申请日：1975-03-21
申请人： James L. Braswell , Cecil E. Covington , Nolan B. Phillips , Reggie J. Tomerlin , Robert M. Wohlfeld
发明人： James L. Braswell , Cecil E. Covington , Nolan B. Phillips , Reggie J. Tomerlin , Robert M. Wohlfeld
IPC分类号： F04D29/38 , B29D99/00 , B64C27/46 , B64C27/473 , B64C27/32
CPC分类号： B29D99/0025 , B64C27/473 , B64C2027/4736 , Y10T428/24149
摘要： A composite rotor blade has a nose spar of fiber reinforced plastic with the fibers extending spanwise the length of the spar and at the root encircling a transverse hub attachment structure with the spar provided with a tubular inner liner of cross ply filament wound fiberglass forming a closure for the nose spar with a blad afterbody structure including skins for integrating the afterbody with the nose spar and liner. Preferably the spar has an inner liner and an outer liner both of cross ply filament wound fiberglass in multi layers. The blade afterbody structure includes honeycomb filler having cells extending in the direction of blade thickness.
摘要翻译：复合转子叶片具有纤维增强塑料的鼻梁，纤维沿着翼梁的长度方向延伸，并且在根部处包围横向轮毂安装结构，翼梁设置有形成封闭件的交叉层缠绕玻璃纤维的管状内衬层用于具有平坦后身体结构的鼻梁，包括用于将后身与鼻梁和衬垫整合的皮肤。优选地，翼梁具有内衬和外衬层，两层帘布层缠绕在多层的玻璃纤维上。叶片后体结构包括具有沿叶片厚度方向延伸的孔的蜂窝填料。

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