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1. 发明申请

WO2013152300A3 MOTION CONTROLLED HELICOPTER AND ROTATION RATE SWITCHED FLUID LEAD LAG DAMPER 审中-公开
标题翻译：运动控制直升机和旋转速率切换流体导管拉杆阻尼器
公开(公告)号：WO2013152300A3
公开(公告)日：2013-12-27
申请号：PCT/US2013035468
申请日：2013-04-05
申请人： LORD CORP , FUHRER ZACHARY , JOLLY MARK , MARR CONOR
发明人： FUHRER ZACHARY , JOLLY MARK , MARR CONOR
IPC分类号： B64C27/51 , F16F9/504
CPC分类号： B64C27/51 , B64C27/32 , F16F9/064 , F16F9/20 , F16F9/504 , F16F13/08 , F16F2230/16
摘要： A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR).
摘要翻译：公开了一种用于控制直升机地面共振和空气共振运动的方法以及离心力开关阻尼器。直升机牵引滞后阻尼器（30）具有第一接地共振运动阻尼速率级（FDR）和第二空气谐振运动阻尼速率级（SDR）。阻尼器（30）包括离心力开关（52）。阻尼器（30）相对于旋转翼旋转轴线（26）和直升机叶片（24）定向。离心力切换阻尼器30的飞行中旋转速度致动离心力开关52，其中阻尼器从第一接地共振运动阻尼率阶段（FDR）切换到第二空气共振运动阻尼速率级（SDR ）。

2. 发明申请

WO2012138816A3 ROTARY WING AIRCRAFT INSTRUMENTED MOTION CONTROL BEARINGS 审中-公开
标题翻译：旋转飞行器仪表运动控制轴承
公开(公告)号：WO2012138816A3
公开(公告)日：2014-05-08
申请号：PCT/US2012032249
申请日：2012-04-05
申请人： ALLRED CHARLES , DOWNING MARSHALL , FUHRER ZACHARY , JOLLY MARK , SMITH MATTHEW , LORD CORP
发明人： ALLRED CHARLES , DOWNING MARSHALL , FUHRER ZACHARY , JOLLY MARK , SMITH MATTHEW
IPC分类号： B64C27/35 , F16F1/41
CPC分类号： F16C27/06 , B64C27/35 , F16F1/41 , Y10T29/49643
摘要： Motion control bearings and methods making such with the capability to monitor properties therein is provided. Devices and methods for creating and using motion control bearings for rotary wing aircraft in particular are disclosed using wireless communication and monitoring of multiple load, motion and health related information items related to the bearing and blade at the wing hub. Static and dynamic blade orientation provides additional information on flight regime, thrust vectors, and gross vehicle weight. Power is provided using kinetic energy power harvesting.
摘要翻译：提供了运动控制轴承和使其具有监控其性能的方法。特别是用于创建和使用用于旋翼飞机的运动控制轴承的装置和方法公开了使用无线通信和监视与翼中心轴承和叶片相关的多个负载，运动和健康相关信息项。静态和动态叶片方向提供有关飞行状态，推力矢量和车辆总重量的更多信息。使用动能收集功率提供动力。

3. 发明申请

WO2007140362A9 ROTARY WING AIRCRAFT ROTARY LEAD LAG DAMPER 审中-公开
标题翻译：旋转翼飞机旋转导杆拉杆阻尼器
公开(公告)号：WO2007140362A9
公开(公告)日：2008-04-03
申请号：PCT/US2007069871
申请日：2007-05-29
申请人： LORD CORP , JONES PETER J , FUHRER ZACHARY
发明人： JONES PETER J , FUHRER ZACHARY
IPC分类号： B64C27/00 , B64C27/51
CPC分类号： B64C27/51 , F16F9/145
摘要： The invention provides a rotary damper (20) for controlling helicopter motions. The rotary damper includes an outer canister (22) with an inner paddle wheel receiving cavity (26) which receives an inner paddle wheel (60) with upper and lower elastomeric tubular intermediate members (78,80) between the inner paddle wheel and the outer canister. The canister and inner paddle wheel form neighboring variable volume chambers (82,84) in liquid communication through liquid damping conduits. A clockwise rotation of the inner paddle wheel about the center of rotation axis (28) relative to the outer canister pumps damper liquid from a second variable volume chamber through a first liquid conduit towards a first variable volume chamber, and a counterclockwise rotation of the paddle wheel relative to the outer canister pumps the damper liquid from the first variable volume chamber through the first liquid conduit towards the second variable volume chamber with the elastomeric tubular intermediate members providing for the relative rotation and containing the damper liquid in the damper.
摘要翻译：本发明提供一种用于控制直升机运动的旋转阻尼器（20）。旋转阻尼器包括具有内桨叶容纳腔（26）的外筒（22），其接纳内桨轮（60），所述内桨轮（60）具有在内桨叶轮和外桨轮之间的上和下弹性体管状中间构件（78,80）罐。罐和内桨轮形成通过液体阻尼管道液体连通的相邻的可变体积腔室（82,84）。内侧叶轮围绕旋转轴线（28）的中心相对于外部罐泵顺时针旋转，从第二可变容积室将液体通过第一液体导管朝向第一可变容积腔室缓冲液体，并且桨叶的逆时针旋转相对于外筒的车轮将来自第一可变容积室的阻尼液通过第一液体管道朝向第二可变容积室泵送，弹性体管状中间构件提供相对旋转并将阻尼液体容纳在阻尼器中。

4. 发明申请

WO2007140362A3 ROTARY WING AIRCRAFT ROTARY LEAD LAG DAMPER 审中-公开
标题翻译：旋翼式飞机旋转铅延迟器
公开(公告)号：WO2007140362A3
公开(公告)日：2008-01-17
申请号：PCT/US2007069871
申请日：2007-05-29
申请人： LORD CORP , JONES PETER J , FUHRER ZACHARY
发明人： JONES PETER J , FUHRER ZACHARY
IPC分类号： B64C27/00 , B64C27/51
CPC分类号： B64C27/51 , F16F9/145
摘要： The invention provides a rotary damper (20) for controlling helicopter motions. The rotary damper includes an outer canister (22) with an inner paddle wheel receiving cavity (26) which receives an inner paddle wheel (60) with upper and lower elastomeric tubular intermediate members (78,80) between the inner paddle wheel and the outer canister. The canister and inner paddle wheel form neighboring variable volume chambers (82,84) in liquid communication through liquid damping conduits. A clockwise rotation of the inner paddle wheel about the center of rotation axis (28) relative to the outer canister pumps damper liquid from a second variable volume chamber through a first liquid conduit towards a first variable volume chamber, and a counterclockwise rotation of the paddle wheel relative to the outer canister pumps the damper liquid from the first variable volume chamber through the first liquid conduit towards the second variable volume chamber with the elastomeric tubular intermediate members providing for the relative rotation and containing the damper liquid in the damper.
摘要翻译：本发明提供了一种用于控制直升机运动的旋转阻尼器（20）。旋转阻尼器包括带有内叶轮容纳空腔（26）的外罐（22），该内叶轮容纳空腔容纳内叶轮（60），在内叶轮和外叶轮之间具有上部和下部弹性管状中间构件（78,80）罐。罐和内桨叶形成通过液体阻尼导管液体连通的相邻可变容积腔室（82,84）。内叶轮围绕旋转轴线（28）的中心相对于外罐的顺时针旋转将阻尼器液体从第二可变容积室通过第一液体导管朝向第一可变容积室泵送，并且桨的逆时针旋转轮相对于外罐从第一可变容积腔室通过第一液体导管泵送阻尼器液体朝向第二可变容积腔室，其中弹性管状中间构件提供相对旋转并且将阻尼器液体容纳在阻尼器中。

5. 发明申请

WO2013062735A3 RISER TENSIONER SYSTEM FOR OFF SHORE OIL PLATFORMS AND PETROLEUM PRODUCTION PROCESSES 审中-公开
标题翻译：用于离岸油平台和石油生产过程的升降机系统
公开(公告)号：WO2013062735A3
公开(公告)日：2014-01-09
申请号：PCT/US2012059020
申请日：2012-10-05
申请人： LORD CORP , JONES PETER , CUNE GREGG , FUHRER ZACHARY , OWENS JONATHAN
发明人： JONES PETER , CUNE GREGG , FUHRER ZACHARY , OWENS JONATHAN
IPC分类号： E21B19/00
CPC分类号： E21B19/006 , E21B19/002
摘要： A riser tensioner system (100) and method of making is provided. In the field of underwater petroleum production, petroleum wells and offshore platforms heavy structures are used to extract the petroleum from the ocean floor. These heavy structures use riser tensioner systems. The present invention provides an elastomeric bearing riser tensioner systems and that is resistant to corrosion and does not need lubrication. The elastomeric bearings use a combination of nonelastomeric shims (118) and elastomer material (116) bonded between bearing members (112, 114), which are capable of being attached to the riser tensioners.
摘要翻译：提供了提升器张紧器系统（100）和制造方法。在水下石油生产领域，石油井和海上平台重型结构用于从海底提取石油。这些重型结构使用立管张紧器系统。本发明提供一种弹性轴承立管张紧器系统，并且其耐腐蚀并且不需要润滑。弹性体轴承使用结合在轴承构件（112,114）之间的非弹性垫片（118）和弹性体材料（116）的组合，其能够附接到立管张紧器。

6. 发明申请

WO2011062639A3 A ROTARY WING AIRCRAFT BEARING FOR ROTARY WING AIRCRAFT MOTIONS 审中-公开
标题翻译：旋转式飞机轴承用于旋转式飞机运动
公开(公告)号：WO2011062639A3
公开(公告)日：2011-10-20
申请号：PCT/US2010003024
申请日：2010-11-23
申请人： LORD CORP , HALLADAY JAMES R , SHERIDAN PATRICK M , DOWNING MARSHALL W , FUHRER ZACHARY
发明人： HALLADAY JAMES R , SHERIDAN PATRICK M , DOWNING MARSHALL W , FUHRER ZACHARY
IPC分类号： B64C27/35 , F16F1/40
CPC分类号： F16C41/008 , B64C27/35 , F16C33/04 , F16F1/406
摘要： A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface. At least one of the elastomeric shim members layers has an interior elastomer region distal from the exterior surface, the interior elastomer region formed an interior cured elastomer composition having at least a first interior optical characteristic ingredient, and an exterior elastomer region encompassing the interior elastomer region, the exterior elastomer region proximate the exterior surface, the exterior elastomer region formed from an exterior cured elastomer composition having at least a second exterior optical characteristic ingredient, the at least second exterior optical characteristic ingredient different than the interior cured elastomer composition first interior optical characteristic ingredient, wherein with an elastomer void crack propagating from the exterior surface inward towards the interior elastomer region and a repeated rotary wing aircraft relative motion between the first rotary wing aircraft member and the second rotary wing aircraft member generates a plurality of interior cured elastomer composition crumbs to be expelled from the elastomer void, the interior cured elastomer composition crumbs optically distinguishable from the exterior cured elastomer composition.
摘要翻译：一种旋转翼飞行器轴承，其在第一旋转翼飞行器构件和第二旋转翼飞行器构件之间提供受限的相对运动。轴承包括弹性体模具粘结的层压轴承堆叠，弹性体模具粘合的层压轴承堆叠包括多个模具粘结的非弹性垫片构件层和弹性垫片构件层的交替层，交替层具有远离外部表面和内部中心外表面。弹性垫片构件层中的至少一个具有远离外表面的内部弹性体区域，内部弹性体区域形成内部固化的弹性体组合物，其具有至少第一内部光学特性成分和包围内部弹性体区域的外部弹性体区域，靠近外表面的外部弹性体区域，由外部固化的弹性体组合物形成的外部弹性体区域，其具有至少第二外部光学特征成分，所述至少第二外部光学特性成分不同于内部固化的弹性体组合物的第一内部光学特性成分，其中弹性体空隙裂纹从外表面向内传播到内部弹性体区域，并且重复的旋转翼飞行器在第一旋转翼飞行器构件和第二旋翼飞行器构件之间的相对运动产生多叶内部固化的弹性体组合物碎屑从弹性体空隙排出，内部固化的弹性体组合物与外部固化的弹性体组合物可光学地区分开。

7. 发明申请

WO2011062639A9 A ROTARY WING AIRCRAFT BEARING FOR ROTARY WING AIRCRAFT MOTIONS 审中-公开
标题翻译：用于旋翼飞机运动的旋翼飞机轴承
公开(公告)号：WO2011062639A9
公开(公告)日：2011-07-21
申请号：PCT/US2010003024
申请日：2010-11-23
申请人： LORD CORP , HALLADAY JAMES R , SHERIDAN PATRICK M , DOWNING MARSHALL W , FUHRER ZACHARY
发明人： HALLADAY JAMES R , SHERIDAN PATRICK M , DOWNING MARSHALL W , FUHRER ZACHARY
IPC分类号： B64C27/35
CPC分类号： F16C41/008 , B64C27/35 , F16C33/04 , F16F1/406
摘要： A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface. At least one of the elastomeric shim members layers has an interior elastomer region distal from the exterior surface, the interior elastomer region formed an interior cured elastomer composition having at least a first interior optical characteristic ingredient, and an exterior elastomer region encompassing the interior elastomer region, the exterior elastomer region proximate the exterior surface, the exterior elastomer region formed from an exterior cured elastomer composition having at least a second exterior optical characteristic ingredient, the at least second exterior optical characteristic ingredient different than the interior cured elastomer composition first interior optical characteristic ingredient, wherein with an elastomer void crack propagating from the exterior surface inward towards the interior elastomer region and a repeated rotary wing aircraft relative motion between the first rotary wing aircraft member and the second rotary wing aircraft member generates a plurality of interior cured elastomer composition crumbs to be expelled from the elastomer void, the interior cured elastomer composition crumbs optically distinguishable from the exterior cured elastomer composition.
摘要翻译：提供第一旋翼飞机构件和第二旋翼飞机构件之间受约束的相对运动的旋翼飞机轴承。所述轴承包括弹性体模制结合的叠层轴承叠层，所述弹性体模制结合叠层轴承叠层包括多个非弹性垫片构件层和弹性体垫片构件层的多个模制结合的交替层，所述交替层具有外表面和远离外表面。至少一个弹性垫片构件层具有远离外表面的内部弹性体区域，内部弹性体区域形成为具有至少第一内部光学特性成分的内部固化弹性体组合物，以及包围内部弹性体区域的外部弹性体区域，所述外部弹性体区域靠近所述外部表面，所述外部弹性体区域由外部固化的弹性体组合物形成，所述外部固化的弹性体组合物具有至少第二外部光学特征成分，所述至少第二外部光学特征成分不同于所述内部固化的弹性体组合物其中随着从外表面向内朝向内部弹性体区域传播的弹性体空隙裂缝以及第一旋翼飞行器构件和第二旋翼飞机构件之间的重复的旋翼飞行器相对运动产生一个套筒内部固化的弹性体组合物碎屑从弹性体空隙排出，内部固化的弹性体组合物碎屑与外部固化的弹性体组合物光学区分。

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