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1. 发明授权

US09352830B2 Aircraft rotor with discrete flap hinge 有权
标题翻译：具有离散翼片铰链的飞机转子
公开(公告)号：US09352830B2
公开(公告)日：2016-05-31
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： B64C27/39 , B64C27/48
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。

2. 发明授权

US08657228B2 Method and apparatus for actively manipulating aerodynamic surfaces 有权
标题翻译：用于主动操纵气动表面的方法和装置
公开(公告)号：US08657228B2
公开(公告)日：2014-02-25
申请号：US13577633
申请日：2010-11-04
申请人： Troy C. Schank , Peter H. Kitzinger , Paul B. Sherrill , Thomas C. Parham , David A. Popelka
发明人： Troy C. Schank , Peter H. Kitzinger , Paul B. Sherrill , Thomas C. Parham , David A. Popelka
IPC分类号： B64C3/50 , B64C9/00 , B64C27/615
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7266 , B64C2027/7272 , Y02T50/34
摘要： A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a cross-axis flexure pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
摘要翻译：提供了一种方法和装置，包括可以连接到翼架以用于控制有源元件的致动器系统。致动器系统可以包括可沿着平行于机翼的跨度轴线的轴线移动的滑动元件。滑动元件可以连接到固定元件和曲柄元件，曲柄元件通常包括梁元件和横轴挠曲枢轴元件。梁元件可以从枢转元件偏移，使得曲柄元件可以在倾向于将滑动元件拉离固定元件的外力作用下具有负刚度的情况下围绕枢转元件旋转。

3. 发明授权

US07828525B2 Soft in-plane tiltrotor hub 有权
标题翻译：柔软的平面倾斜旋转轮毂
公开(公告)号：US07828525B2
公开(公告)日：2010-11-09
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, Jr. , 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, Jr. , David A. Popelka , Ernst C. Schellhase , Charles L. Hollimon , Thomas J. Newman , Bryan Baskin , Thomas C. Campbell , Daniel B. Robertson
IPC分类号： B64C27/51
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. 发明申请

US20100021301A1 Step-Over Blade-Pitch Control System 有权
标题翻译：叶片间距控制系统
公开(公告)号：US20100021301A1
公开(公告)日：2010-01-28
申请号：US12446597
申请日：2006-12-08
申请人： Frank B. Stamps , Rlohard E. Rauber , David A. Popelka , Patrick R. Tisdale , Thomas C. Campbell , James L. Braswell, JR. , Keith Stanney , Mark Wasikowski , Tom Donovan , Bryan Baskin , Ryan Smith
发明人： Frank B. Stamps , Rlohard E. Rauber , David A. Popelka , Patrick R. Tisdale , Thomas C. Campbell , James L. Braswell, JR. , Keith Stanney , Mark Wasikowski , Tom Donovan , Bryan Baskin , Ryan Smith
IPC分类号： B64C27/54
CPC分类号： B64C11/30 , B64C27/605 , B64C29/0033
摘要： A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.
摘要翻译：用于飞行器转子上的叶片的俯仰控制系统具有连接到轮毂并且能够相对于轮毂围绕枢转轴线枢转的槌球转子轮毂（31）和多个步进臂（61）。多个节距连杆（55）中的每一个将步进臂（61）中的一个连接到飞行控制系统，用于响应于输入而围绕枢转轴线和相对于轮毂枢转连接的分离臂（61）从控制系统。多个翻转链节（69）中的每一个将分阶臂（61）中的一个连接到其中一个叶片，用于响应于相关联的分步臂的枢转而围绕俯仰轴旋转相关叶片。

5. 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。

6. 发明授权

US08474745B2 Rotor hub vibration attenuator 有权
公开(公告)号：US08474745B2
公开(公告)日：2013-07-02
申请号：US13076581
申请日：2011-03-31
申请人： David A. Popelka , Frank B. Stamps
发明人： David A. Popelka , Frank B. Stamps
IPC分类号： B64C27/06 , B64C27/51
CPC分类号： B64C27/001 , B64C11/008 , B64C29/0033 , B64C2027/003
摘要： A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe.

7. 发明授权

US08287237B2 Step-over blade-pitch control system 有权
标题翻译：分步桨叶桨距控制系统
公开(公告)号：US08287237B2
公开(公告)日：2012-10-16
申请号：US12446597
申请日：2006-12-08
申请人： Frank B. Stamps , Richard E. Rauber , David A. Popelka , Patrick R. Tisdale , Thomas C. Campbell , Keith Stanney , James L. Braswell, Jr. , Mark Wasikowski , Tom Donovan , Bryan Baskin , John J. Corrigan, III , Ryan Smith
发明人： Frank B. Stamps , Richard E. Rauber , David A. Popelka , Patrick R. Tisdale , Thomas C. Campbell , Keith Stanney , James L. Braswell, Jr. , Mark Wasikowski , Tom Donovan , Bryan Baskin , John J. Corrigan, III , Ryan Smith
IPC分类号： B64C11/06
CPC分类号： B64C11/30 , B64C27/605 , B64C29/0033
摘要： A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.
摘要翻译：用于飞行器转子上的叶片的俯仰控制系统具有连接到轮毂并且能够相对于轮毂围绕枢转轴线枢转的槌球转子轮毂（31）和多个步进臂（61）。多个节距连杆（55）中的每一个将步进臂（61）中的一个连接到飞行控制系统，用于响应于输入而围绕枢转轴线和相对于轮毂枢转连接的分离臂（61）从控制系统。多个翻转链节（69）中的每一个将分阶臂（61）中的一个连接到其中一个叶片，用于响应于相关联的分步臂的枢转而围绕俯仰轴旋转相关叶片。

8. 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。

9. 发明授权

US4601639A Nodalized rotor 失效
标题翻译：节点转子
公开(公告)号：US4601639A
公开(公告)日：1986-07-22
申请号：US590987
申请日：1984-03-19
申请人： Jing G. Yen , David A. Popelka
发明人： Jing G. Yen , David A. Popelka
IPC分类号： B64C27/51 , B64C27/33 , B64C27/473 , B64C27/46
CPC分类号： B64C27/33 , B64C27/473
摘要： A nodalized rotor system is provided for a multi-bladed helicopter. Equally spaced radial arms each have an inboard flapping section to accommodate beam-wise blade flapping and an outboard flex section to accommodate pitch changes. A blade is coupled to the end of each arm with a cuff and pitch horn rigidly connected to the blade and pivotally connected to its arm in the region of the flapping section. The blade has a concentration of weight over the section of blade extending from about 32% to 42% of the hub-blade radius of running weight four times the running weight at 50% of the hub-blade radius. Said blade has a reduced mass at outboard 30% of the hub-blade radius, at a level of 80% of the running weight at 50% of the hub-blade radius.
摘要翻译：为多叶直升机提供了一个节点转子系统。同样间隔的径向臂各具有内侧振荡部分，以适应束流式叶片拍动和外侧弯曲部分以适应间距变化。刀片连接到每个臂的端部，其中袖带和节距角刚性地连接到刀片并且在拍动部分的区域中枢转地连接到其臂。叶片的重量比在叶片截面上的重量的重量从轮毂叶片半径的50％处的行进重量的四倍的轮毂叶片半径的大约32％到42％的四倍。所述叶片在轮毂叶片半径的30％处具有减小的质量，在轮毂叶片半径的50％处的运动重量的80％的水平。

10. 发明授权

US09481455B2 Dual series damper system 有权
标题翻译：双系列阻尼器系统
公开(公告)号：US09481455B2
公开(公告)日：2016-11-01
申请号：US13703650
申请日：2011-04-26
申请人： Mithat Yuce , David A. Popelka , Frank B. Stamps , Mark A. Wiinikka
发明人： Mithat Yuce , David A. Popelka , Frank B. Stamps , Mark A. Wiinikka
IPC分类号： B64C27/51 , F16F13/06
CPC分类号： B64C27/51 , F16F13/06
摘要： A dual series damper includes a fluid damper portion and a elastomeric damper portion. The fluid damper portion includes a first housing, a first connection member, and a piston coupled to the first connection member. The piston divides an interior of the first housing into a first fluid chamber and a second fluid chamber. The piston has a fluid passage in the piston, the fluid passage being configured to provide fluid communication between the first fluid chamber and the second fluid chamber. The elastomeric damper portion includes a second housing, a second connection member coupled to the second housing, and an elastomer between the first housing and the second housing. When a lead/lag force is introduced to the dual series damper, the fluid damper portion behaves rigidly so that the elastomeric damper portion dampens the lead/lag oscillation.
摘要翻译：双串联阻尼器包括流体阻尼器部分和弹性阻尼器部分。流体阻尼器部分包括第一壳体，第一连接构件和联接到第一连接构件的活塞。活塞将第一壳体的内部分成第一流体室和第二流体室。活塞在活塞中具有流体通道，流体通道构造成在第一流体室和第二流体室之间提供流体连通。弹性阻尼器部分包括第二壳体，联接到第二壳体的第二连接构件和在第一壳体和第二壳体之间的弹性体。当引入/滞后力被引入双串联阻尼器时，流体阻尼器部分刚性地运动，使得弹性阻尼器部分阻尼引导/滞后振荡。

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