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1. 发明申请

WO2005049421A3 SOFT IN-PLANE ROTOR HUB 审中-公开
公开(公告)号：WO2005049421A3
公开(公告)日：2005-06-02
申请号：PCT/US2004/027990
申请日：2004-08-27
申请人： BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
发明人： STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
IPC分类号： B64C27/51
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.

2. 发明申请

WO2005021990A2 DUAL SPRING RATE DAMPER 审中-公开
标题翻译：双弹簧阻尼器
公开(公告)号：WO2005021990A2
公开(公告)日：2005-03-10
申请号：PCT/US2004/027964
申请日：2004-08-27
申请人： BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
发明人： STAMPS, Frank, B. , SMITH, Michael, R. , BOTHWELL, Christopher, M. , CORSO, Lawrence, M. , BRASWELL, James, L., Jr. , POPELKA, David, A. , SCHELLHASE, Ernst, C. , HOLLIMON, Charles, L. , NEWMAN, Thomas, J. , BASKIN, Bryan , CAMPBELL, Thomas, C. , ROBERTSON, Daniel, B.
IPC分类号： F16D
CPC分类号： F16F13/08 , B64C27/35 , B64C27/39 , B64C27/51 , F16F13/24 , F16F13/26 , F16F2230/30
摘要： A damper has a piston having an axis, an outer surface, and opposing ends. Elastomeric seals are in sealing contact with the outer surface of the piston, the seals being coaxial with the piston and limiting movement of the piston to a path along the axis of the piston. The seals also define fluid chambers adjacent the ends of the piston. A primary passage communicates the fluid chambers, and a selectively switchable valve for controls a flow of fluid from one of the chambers to another of the chambers through the primary passage. When the flow of fluid through the primary passage is permitted, movement of the piston is resisted by a first spring rate due to a shear force required to cause shear deflection of the seals. When the flow of fluid through the primary passage is restricted, movement of the piston is resisted by a second spring rate due to a fluid force required to cause bulging deflection of the seals.
摘要翻译：阻尼器具有具有轴线，外表面和相对端的活塞。弹性密封件与活塞的外表面密封接触，密封件与活塞同轴并且限制活塞沿着活塞轴线的路径运动。密封件还限定了邻近活塞端部的流体室。主要通道连通流体室，以及可选择地可切换的阀，用于控制通过主通道从一个室到另一个室的流体流。当允许通过主通道的流体流动时，活塞的运动由于需要剪切力而引起密封件的剪切偏转而抵抗第一弹簧刚度。当通过主通道的流体流被限制时，活塞的运动由于需要使密封件凸起偏转所需的流体力而受到第二弹簧刚度的抵抗。

3. 发明申请

WO2008073073A3 STEP-OVER BLADE-PITCH CONTROL SYSTEM 审中-公开
公开(公告)号：WO2008073073A3
公开(公告)日：2008-06-19
申请号：PCT/US2006/046099
申请日：2006-12-08
申请人： BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , RAUBER, Richard, E. , POPELKA, David, A. , TISDALE, Patrick, R. , CAMPBELL, Thomas, C. , BRASWELL, James, L., Jr. , STANNEY, Keith , WASIKOWSKI, Mark , DONOVAN, Tom , BASKIN, Bryan , SMITH, Ryan , CORRIGAN, John, J., III.
发明人： STAMPS, Frank, B. , RAUBER, Richard, E. , POPELKA, David, A. , TISDALE, Patrick, R. , CAMPBELL, Thomas, C. , BRASWELL, James, L., Jr. , STANNEY, Keith , WASIKOWSKI, Mark , DONOVAN, Tom , BASKIN, Bryan , SMITH, Ryan , CORRIGAN, John, J., III.
IPC分类号： B64C27/54 , F03B3/14
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.

4. 发明申请

WO2007081337A3 STIFF-IN-PLANE GIMBALED TILTROTOR HUB 审中-公开
公开(公告)号：WO2007081337A3
公开(公告)日：2007-07-19
申请号：PCT/US2006/001082
申请日：2006-01-13
申请人： BELL HELICOPTER TEXTRON INC. , RAUBER, Richard, E. , BRASWELL, James, L., Jr. , CAMPBELL, Thomas, C. , POPELKA, David, A. , SOUTHERLAND, Michael, J. , STAMPS, Frank, B. , STANNEY, Keith , TISDALE, Patrick, R. , WASIKOWSKI, Mark
发明人： RAUBER, Richard, E. , BRASWELL, James, L., Jr. , CAMPBELL, Thomas, C. , POPELKA, David, A. , SOUTHERLAND, Michael, J. , STAMPS, Frank, B. , STANNEY, Keith , TISDALE, Patrick, R. , WASIKOWSKI, Mark
IPC分类号： B64C27/48
摘要： A rotor-hub for a rotary-wing aircraft is disclosed. The rotor-hub comprises a yoke comprising a plurality of yoke arms and a plurality of yoke straps, wherein the yoke arms are joined together by the yoke straps, and wherein a plurality of inner walls of the yoke define a central void space. A pitch horn is movably connected to the yoke and a portion of the pitch horn is located within the central void space. A connecting shell is fixedly attached to the yoke.

5. 发明申请

WO2007133735A2 YOKE WITH NOTCHED ARM ROOTS 审中-公开
标题翻译：与备注的ARM ROOTS
公开(公告)号：WO2007133735A2
公开(公告)日：2007-11-22
申请号：PCT/US2007/011532
申请日：2007-05-14
申请人： BELL HELICOPTER TEXTRON INC. , STAMPS, Frank, B. , RAUBER, Richard, E. , POPELKA, David, A. , CAMPBELL, Thomas, C. , DONOVAN, Tom , TISDALE, Patrick, R.
发明人： STAMPS, Frank, B. , RAUBER, Richard, E. , POPELKA, David, A. , CAMPBELL, Thomas, C. , DONOVAN, Tom , TISDALE, Patrick, R.
IPC分类号： A63B21/02 , A63B21/04
CPC分类号： B64C27/33 , B64C27/32 , B64C29/0033
摘要： A yoke for a rotary wing aircraft rotor system has a plurality of arms, each arm having a root. Each root has a notched portion configured to allow passage of a portion of a blade-pitch control system through the notched portion.
摘要翻译：用于旋翼飞机转子系统的轭具有多个臂，每个臂具有根部。每个根部具有被配置为允许叶片间距控制系统的一部分通过切口部分的切口部分。

6. 发明申请

WO2008133614A1 ROTOR HUB VIBRATION ATTENUATOR 审中-公开
标题翻译：转子座振动衰减器
公开(公告)号：WO2008133614A1
公开(公告)日：2008-11-06
申请号：PCT/US2007/010109
申请日：2007-04-24
申请人： BELL HELICOPTER TEXTRON INC. , RAUBER, Richard, E. , POPELKA, David, A. , STAMPS, Frank, B.
发明人： RAUBER, Richard, E. , POPELKA, David, A. , STAMPS, Frank, B.
IPC分类号： B64C27/32 , F16C15/00
CPC分类号： B64C27/32 , B06B1/164 , B64C27/001 , B64C2027/003 , B64C2027/004 , F16F7/1011 , F16F15/14
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.
摘要翻译：用于飞行器的振动衰减器具有安装在飞行器的转子轮毂的旋转系统中的至少一个重量，每个重量可围绕毂相对于轮毂的旋转轴线和彼此的重量旋转。提供驱动装置，用于以选定的速度围绕旋转轴线旋转每个重量，以产生相对于和衰减具有所选频率的转子引起的振动的振荡剪切力。

7. 发明申请

WO2012148389A1 DUAL SERIES DAMPER SYSTEM 审中-公开
标题翻译：双系列阻尼器系统
公开(公告)号：WO2012148389A1
公开(公告)日：2012-11-01
申请号：PCT/US2011/033956
申请日：2011-04-26
申请人： BELL HELICOPTER TEXTRON INC. , YUCE, Mithat , POPELKA, David, A. , STAMPS, Frank, B. , WIINIKKA, Mark, A.
发明人： YUCE, Mithat , POPELKA, David, A. , STAMPS, Frank, B. , WIINIKKA, Mark, A.
IPC分类号： B64C27/51
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以及在第一壳体和第二壳体之间的弹性体。当引导/滞后力被引入双重串联阻尼器时，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。

8. 发明申请

WO2012060836A1 METHOD AND APPARATUS FOR ACTIVELY MANIPULATING AERODYNAMIC SURFACES 审中-公开
标题翻译：用于动态操纵气动表面的方法和装置
公开(公告)号：WO2012060836A1
公开(公告)日：2012-05-10
申请号：PCT/US2010/055367
申请日：2010-11-04
申请人： BELL HELICOPTER TEXTRON INC. , SCHANK, Troy, C. , KINTZINGER, Peter, H. , SHERRILL, Paul, B. , PARHAM, Thomas, C. , POPELKA, David, A.
发明人： SCHANK, Troy, C. , KINTZINGER, Peter, H. , SHERRILL, Paul, B. , PARHAM, Thomas, C. , POPELKA, David, A.
IPC分类号： B64C27/00
CPC分类号： B64C13/26 , B64C13/30 , B64C27/00 , B64C27/001 , B64C27/615 , B64C2027/7266 , F16H21/44 , Y02T50/34 , Y02T50/44
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。

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