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81. 发明授权

US08956117B2 Stiff-in-plane rotor configuration 有权
标题翻译：刚体平面转子配置
公开(公告)号：US08956117B2
公开(公告)日：2015-02-17
申请号：US13144448
申请日：2009-01-19
申请人： Frank B. Stamps , Patrick R. Tisdale , Tom Donovan , Richard E. Rauber
发明人： Frank B. Stamps , Patrick R. Tisdale , Tom Donovan , Richard E. Rauber
IPC分类号： B64C27/33 , B64C27/32
CPC分类号： B64C27/35 , B64C27/32 , B64C27/33 , B64C27/39 , B64C27/48
摘要： A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.
摘要翻译：一种用于旋转翼飞行器的转子组件，该转子具有中心轮毂组件，其具有带有多个臂的挠曲型扭转柄轭，每个臂适于安装在其上的转子叶片。臂通过扭转相应的俯仰轴线的臂的部分来提供附接到轭的叶片的桨距变化。与每个臂相关联的内侧变桨轴承附接到轮毂组件并且允许所附接的叶片围绕俯仰轴线旋转，内侧变桨轴承还允许臂相对于轮毂组件的平面外运动绕一个拍动轴。与每个臂相关联的外侧变桨轴承从相对于内侧变桨轴承的选定距离附接到相关联的臂，并且允许所附接的叶片围绕桨距轴线旋转。

82. 发明申请

US20130287576A1 Aircraft Rotor with Discrete Flap Hinge 有权
标题翻译：飞机转子与离散瓣铰链
公开(公告)号：US20130287576A1
公开(公告)日：2013-10-31
申请号：US13455814
申请日：2012-04-25
申请人： Frank B. Stamps , David A. Popelka , Tom Donovan , Patrick R. Tisdale , Richard E. Rauber
发明人： Frank B. Stamps , David A. Popelka , Tom Donovan , Patrick R. Tisdale , Richard E. Rauber
IPC分类号： B64C27/54
CPC分类号： B64C27/39 , B64C27/48
摘要： An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis.
摘要翻译：飞机转子组件具有适于安装到中心转子桅杆上的上和下毂板，以与其一起旋转。多个径向臂连接到安装在轮毂板之间并形成离散的翼片铰链的至少两个翼片轴承，每个翼片铰链限定翼片轴线并允许相关联的臂相对于轮毂板和相应翼片轴线的旋转。多个叶片夹具中的每一个可旋转地连接到一个臂上，用于围绕俯仰轴线旋转，并适于将叶片安装到每个叶片手柄上，使得每个叶片能够围绕俯仰轴线旋转，并且能够与相应的臂相对于轮毂板和围绕相应的翼片轴线旋转。

83. 发明授权

US07909579B2 Rotor head for a twin-rotor helicopter 有权
标题翻译：双转子直升机的转子头
公开(公告)号：US07909579B2
公开(公告)日：2011-03-22
申请号：US11846568
申请日：2007-08-29
申请人： Charles Lin
发明人： Charles Lin
IPC分类号： B64C11/04
CPC分类号： B64C27/39 , Y10S416/50
摘要： A rotor head includes a hub and two joint members. The hub has opposite tubular end portions, each formed with a socket that extends inwardly from an end face thereof along a tube axis and that has inner and outer socket sections. Each of the joint members includes a link and a vibration absorbing component. The link has a hub coupling segment retained rotatably in the inner socket section of a respective socket, an intermediate segment extending from the hub coupling segment and disposed movably in the outer socket section of the respective socket, and a blade coupling segment extending from the intermediate segment and outwardly of the outer socket section. The vibration absorbing component is mounted on the intermediate segment, and is disposed in the outer socket section.
摘要翻译：转子头包括轮毂和两个接头构件。轮毂具有相对的管状端部，每个端部形成有从其端面沿管轴线向内延伸并具有内部和外部插座部分的插座。每个接合构件包括连杆和振动吸收部件。连杆具有可旋转地保持在相应插座的内部插座部分中的毂联接部分，从毂联接部分延伸并且可移动地设置在相应插座的外部插座部分中的中间部分，以及从中间体延伸的叶片联接部分并且外部插座部分的外侧。振动吸收部件安装在中间部分上，并且设置在外部插座部分中。

84. 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。

85. 发明申请

US20060285976A1 Protection system, a bellows hinge, and an aircraft 有权
公开(公告)号：US20060285976A1
公开(公告)日：2006-12-21
申请号：US11450275
申请日：2006-06-12
申请人： Jean-Pierre Jalaguier
发明人： Jean-Pierre Jalaguier
IPC分类号： B64C27/50
CPC分类号： F16C11/0671 , B64C27/39 , F16C11/0614 , F16C2326/43
摘要： In order to protect a hinge, an elastomer confinement structure is provided presenting: upstream and downstream openings; a static cap; an upstream collar; and a hinge bellows. Each opening has a ring for rigidly anchoring to a downstream member of the hinge, and each opening has a ring acting as a rigid receiver. The collar is movable and releasably secured by resilient fastening inspection means.

86. 发明授权

US06309182B1 Helicopter rotor droop stop mechanism 有权
标题翻译：直升机转子下垂停止机构
公开(公告)号：US06309182B1
公开(公告)日：2001-10-30
申请号：US09543838
申请日：2000-04-05
申请人： Neal W. Muylaert
发明人： Neal W. Muylaert
IPC分类号： B64C2738
CPC分类号： B64C27/48 , B64C27/39
摘要： A droop stop mechanism is provided for controlling droop of a rotor assembly in both static and dynamic states. The droop stop mechanism includes a U-shaped pendulum having a pair of spaced apart arms interconnected by a stepped base. One end of each of the arms is pivotally coupled to a body of the rotor hub assembly by a pin. A stop plate is coupled between the arms of the pendulum. A spring seat is coupled to the body of the rotor hub assembly opposite the stop plate. A coil spring is coupled between the spring seat and the stop plate. The stepped base includes a first striker portion for abuttingly engaging a tie bar housing of a rotor blade assembly in a static mode position, and a second striker portion for abuttingly engaging the tie bar housing in a dynamic mode position. The bias of the spring urges the pendulum between the static mode position and the dynamic mode position as centrifugal forces acting on the pendulum change. The spring seat doubles as a stop by abuttingly engaging the stop plate when the pendulum is in the dynamic mode position.
摘要翻译：提供下垂停止机构用于控制静止和动态状态下转子组件的下垂。下垂停止机构包括具有通过阶梯式基座互连的一对间隔开的臂的U形摆。每个臂的一端通过销枢转地联接到转子轮毂组件的主体。止动板联接在摆的臂之间。弹簧座与转子轮毂组件的与止动板相对的主体联接。螺旋弹簧联接在弹簧座和止动板之间。阶梯式底座包括用于将静止模式位置的转子叶片组件的系杆壳体邻接地接合的第一撞击部分，以及用于在动态模式位置中将连杆壳体邻接地接合的第二撞针部分。由于作用在钟摆上的离心力发生变化，弹簧的偏压促使静态模式位置与动态模式位置之间的摆锤。当摆位于动态模式位置时，弹簧座通过与止动板邻接地接合而成为止动件。

87. 发明授权

US5951252A Helicopter flap lock assembly 失效
标题翻译：直升机襟翼锁组件
公开(公告)号：US5951252A
公开(公告)日：1999-09-14
申请号：US928905
申请日：1997-09-12
申请人： Neal W. Muylaert
发明人： Neal W. Muylaert
IPC分类号： B64C27/39 , B64C27/38
CPC分类号： B64C27/39
摘要： A flap lock device for restraining the flapping movement of a main rotor blade assembly on a helicopter. The flap lock device includes an first elongate frame member which extends between a first end and a second end and second elongate frame member which also extends between a first end and a second end. A pivot connection pivotally connects the first end of the first frame member with the first end of the second frame member. An outwardly facing contact pad is coupled to each of the frame members and adapted for contact with various positions on the helicopter. An actuating device interconnects the first and second frame members and is used to forcibly move the contact pads outwardly and into contact with the helicopter. The flap lock device is installed between the main rotor blade assembly and the main rotor assembly to forcibly maintain the main rotor blade assembly against the droop stop mechanism.
摘要翻译：一种用于限制主转子叶片组件在直升机上的拍动运动的翼片锁定装置。翼片锁定装置包括在第一端和第二端之间延伸的第一细长框架构件和在第一端和第二端之间延伸的第二细长框架构件。枢转连接将第一框架构件的第一端与第二框架构件的第一端枢转地连接。面向外的接触垫联接到每个框架构件并且适于与直升机上的各种位置接触。致动装置将第一和第二框架构件互连，并用于将接触垫向外强制地移动并与直升机接触。翼片锁定装置安装在主转子叶片组件和主转子组件之间，以强制地将主转子叶片组件抵靠下垂停止机构保持。

88. 发明授权

US4543040A Helicopter rotor system 失效
标题翻译：直升机转子系统
公开(公告)号：US4543040A
公开(公告)日：1985-09-24
申请号：US429365
申请日：1982-09-30
申请人： Francis H. McArdle , Earl Schneider
发明人： Francis H. McArdle , Earl Schneider
IPC分类号： B64C27/35 , B29C70/34 , B64C27/32 , B64C27/39 , B64C27/48
CPC分类号： B29C70/347 , B64C27/32 , B64C27/39 , B64C27/48 , B29L2031/3088 , Y10T29/49332 , Y10T29/49826
摘要： A rotor hub system for a helicopter in which the rotor hub and pitch housing are fabricated predominately of composite material, the flap hinge, pitch hinge and lead-lag hinge contain elastomeric bearings and one step blade folding in either the forward or aft direction using the same drive system. The rotor hub includes closed loop straps which define generally opposed lugs of the flap hinge, and the pitch housing includes a pair of closed loop straps which define the lugs of the lead-lag hinge and a lug of the flap hinge. The use of composite materials as the predominant material of the rotor hub and the pitch housing results in a highly load redundant structure permitting a reduction in size and number of parts, a reduction in drag, and an increase in reliability and safety.
摘要翻译：用于直升机的转子轮毂系统，其中转子轮毂和桨距壳体主要由复合材料制成，翼片铰链，俯仰铰链和牵引延迟铰链包含弹性体轴承和一个步进叶片在前进或后部方向上折叠，使用相同的驱动系统。转子毂包括限定翼片铰链的大致相对的凸耳的闭环带，并且间距壳体包括一对封闭的环形带，其限定了牵引延迟铰链的凸耳和翼片铰链的凸耳。使用复合材料作为转子毂和间距壳体的主要材料形成高负荷冗余结构，允许减小零件的尺寸和数量，减少阻力，并增加可靠性和安全性。

89. 发明授权

US4542567A Method of fabricating a helicopter rotor hub 失效
标题翻译：制造直升机转子轮毂的方法
公开(公告)号：US4542567A
公开(公告)日：1985-09-24
申请号：US556658
申请日：1983-11-30
申请人： Francis H. McArdle , Earl Schneider
发明人： Francis H. McArdle , Earl Schneider
IPC分类号： B64C27/35 , B29C70/34 , B64C27/32 , B64C27/39 , B64C27/48 , B23P15/04
CPC分类号： B29C70/347 , B64C27/32 , B64C27/39 , B64C27/48 , B29L2031/3088 , Y10T29/49332 , Y10T29/49826
摘要： A rotor hub system for a helicopter in which the rotor hub and pitch housing are fabricated predominately of composite material, the flap hinge, pitch hinge and lead-lag hinge contain elastomeric bearings and one step blade folding in either the forward or aft direction using the same drive system. The rotor hub includes closed loop straps which define generally opposed lugs of the flap hinge, and the pitch housing includes a pair of closed loop straps which define the lugs of the lead-lag hinge and a lug of the flap hinge. The use of composite materials as the predominant material of the rotor hub and the pitch housing results in a highly load redundant structure permitting a reduction in size and number of parts, a reduction in drag, and an increase in reliability and safety.
摘要翻译：用于直升机的转子轮毂系统，其中转子轮毂和桨距壳体主要由复合材料制成，翼片铰链，俯仰铰链和牵引延迟铰链包含弹性体轴承和一个步进叶片在前进或后部方向上折叠，使用相同的驱动系统。转子毂包括限定翼片铰链的大致相对的凸耳的闭环带，并且间距壳体包括一对封闭的环形带，其限定了牵引延迟铰链的凸耳和翼片铰链的凸耳。使用复合材料作为转子毂和间距壳体的主要材料形成高负荷冗余结构，允许减小零件的尺寸和数量，减少阻力，并增加可靠性和安全性。

90. 发明授权

US3589835A Variable stiffness rotor 失效
标题翻译：可变刚度转子
公开(公告)号：US3589835A
公开(公告)日：1971-06-29
申请号：US3589835D
申请日：1969-07-17
申请人： UNITED AIRCRAFT CORP
发明人： LINDEN ARTHUR W
IPC分类号： B64C27/32 , B64C27/39 , B64C29/00 , B64C27/48
CPC分类号： B64C27/39 , B64C27/32 , B64C27/327 , B64C29/0033
摘要： A multibladed rotor having the blades connected to the hub by a hinge mechanism and having a variable stiffness spring extending between the hub and the blade across the hinge mechanism to vary the stiffness of the connection between the blade and the hub.

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