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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
Applicant: 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.
Inventor： 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: B64C27/51
Abstract: 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.
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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
Applicant: 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.
Inventor： 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: F16D
CPC classification number: F16F13/08 , B64C27/35 , B64C27/39 , B64C27/51 , F16F13/24 , F16F13/26 , F16F2230/30
Abstract: 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.
Abstract translation: 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。
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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
Applicant: 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.
Inventor： 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.
Abstract: 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.
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公开(公告)号：EP1658184A2
公开(公告)日：2006-05-24
申请号：EP04786599.3
申请日：2004-08-27
Applicant: Bell Helicopter Textron Inc.
Inventor： 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: B60G13/00
CPC classification number: F16F13/08 , B64C27/35 , B64C27/39 , B64C27/51 , F16F13/24 , F16F13/26 , F16F2230/30
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：EP1658222B1
公开(公告)日：2013-04-03
申请号：EP04819036.7
申请日：2004-08-27
Applicant: Bell Helicopter Textron Inc.
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公开(公告)号：EP2089274A2
公开(公告)日：2009-08-19
申请号：EP06838841.2
申请日：2006-12-08
Applicant: Bell Helicopter Textron Inc.
Inventor： 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.
CPC classification number: B64C11/30 , B64C27/605 , B64C29/0033
Abstract: 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.
Abstract translation: 一种用于飞机转子上的叶片的桨距控制系统具有一个万向球转子轮毂（31）和多个连接到该轮毂并且能够围绕枢转轴线相对于轮毂枢转的跨接臂（61）。 多个俯仰连杆（55）中的每一个将所述跨接臂（61）中的一个连接到飞行控制系统，用于响应于输入使所连接的跨接臂（61）绕枢转轴线并且相对于轮毂枢转 来自控制系统。 多个跨接连杆（69）中的每一个将一个跨接臂（61）连接到叶片中的一个，以响应于相关联的跨接臂的枢转而使关联的叶片绕俯仰轴线旋转。
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公开(公告)号：EP1658222A2
公开(公告)日：2006-05-24
申请号：EP04819036.7
申请日：2004-08-27
Applicant: Bell Helicopter Textron Inc.
Inventor： 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: B64C27/51
CPC classification number: F16F13/08 , B64C27/35 , B64C27/39 , B64C27/51 , F16F13/24 , F16F13/26 , F16F2230/30
Abstract: 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.
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公开(公告)号：EP1658184B1
公开(公告)日：2016-10-12
申请号：EP04786599.3
申请日：2004-08-27
Applicant: Bell Helicopter Textron Inc.
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公开(公告)号：EP2089274B1
公开(公告)日：2013-05-22
申请号：EP06838841.2
申请日：2006-12-08
Applicant: Bell Helicopter Textron Inc.
Inventor： 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: B64C11/30 , B64C27/605 , B64C29/00
CPC classification number: B64C11/30 , B64C27/605 , B64C29/0033
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