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1. 发明授权

US5687948A Vibration isolation system including a passive tuned vibration absorber 失效
标题翻译：振动隔离系统包括无源调谐减震器
公开(公告)号：US5687948A
公开(公告)日：1997-11-18
申请号：US533824
申请日：1995-09-26
申请人： Gerald P. Whiteford , Paul T. Herbst
发明人： Gerald P. Whiteford , Paul T. Herbst
IPC分类号： B64D27/26 , F16F1/38 , F16F7/108 , F16M13/00
CPC分类号： B64D27/26 , F16F1/3814 , F16F7/108 , Y02T50/44
摘要： An isolation system (20) including the combination of an elastomeric mount (25) for attachment between a structure (24) and a vibrating member (22) and further including at least one passive tuned vibration absorber (TVA) (32) attached in the proximity the elastomeric mount (25) but on the structure side thereof. The resonant frequency f.sub.r of the passive TVA (32) is tuned to a resonant frequency f.sub.r just below the predominant operating frequency f.sub.o of the vibrating member (22), such that the resonance of the tuned vibration absorber (32) makes the structure (24) appear dynamically stiffer. In particular the ratio of f.sub.r /f.sub.o is in the range of between about 0.90 and 0.90. In one embodiment, the passive TVA (32) attaches directly to the inner member (28) of the elastomeric mount (25) and clamps the TVA assembly (43) to the structure (24) and clamps the structure (24) to the elastomeric mount (25). In another embodiment, the passive TVA (32) is clamped to the structure (24) at a point where it cooperates with the elastomeric mount (25) to reduce transmitted vibration, preferably the TVA (32) is attached at a point within last 20% of the end of the beam-like structure (24).
摘要翻译：一种隔离系统（20），包括用于连接在结构（24）和振动部件（22）之间的弹性支架（25）的组合，并且还包括至少一个被动调谐的振动吸收器（TVA）（32）靠近弹性支架（25），但在其结构侧。无源TVA（32）的谐振频率fr被调谐到刚好低于振动元件（22）的主要工作频率fo的谐振频率fr，使得调谐的振动吸收器（32）的谐振使结构（24 ）出现动态更僵硬。特别地，fr / fo的比率在约0.90和0.90之间。在一个实施例中，无源TVA（32）直接附接到弹性体支架（25）的内部构件（28）并将TVA组件（43）夹紧到结构（24）并将结构（24）夹紧到弹性体（25）。在另一个实施例中，无源TVA（32）在其与弹性体支架（25）配合的点处被夹紧到结构（24），以减少传输的振动，优选地，TVA（32）附接在最后20点波束状结构（24）的端部的％。

2. 发明申请

US20160053557A1 TORSIONAL ISOLATOR 审中-公开
标题翻译：扭转隔离器
公开(公告)号：US20160053557A1
公开(公告)日：2016-02-25
申请号：US14784511
申请日：2014-05-01
申请人： Gerald P. WHITEFORD , Keith R. PTAK , Mark R. JOLLY , Gregg CUNE , LORD Corporation
发明人： Gerald P. WHITEFORD , Keith R. PTAK , Mark R. JOLLY , Gregg CUNE
IPC分类号： E21B17/07 , E21B7/04
CPC分类号： E21B17/07 , E21B7/04
摘要： A torsional isolator (200, 300, 400) designed to reduce vibrations and shock experienced by electronics used during directional drilling is disclosed. The torsional isolator allows the drillstring electronics to oscillate at a slower rotational velocity than the data acquisition rate of associated sensors, such that the sensors record an average value of the azimuth heading thereby allowing for a higher accuracy measurement of the azimuth heading. The sample rate of the sensors is such that the sensors maximum error is reduced by the torsional isolator, as the output angular displacements are lower than the input angular displacements.
摘要翻译：公开了一种扭转隔离器（200,300,400），用于减少在定向钻井期间使用的电子设备所经受的振动和冲击。扭转隔离器允许钻柱电子器件以比相关联的传感器的数据采集速率更慢的旋转速度振荡，使得传感器记录方位角度的平均值，从而允许对方位角的更高精度的测量。传感器的采样率使传感器的最大误差由扭转隔离器减小，因为输出角位移低于输入角位移。

3. 发明申请

US20110084192A1 AIRCRAFT AUXILIARY POWER UNIT SUSPENSION SYSTEM FOR ISOLATING AN AIRCRAFT AUXILIARY POWER UNIT 有权
标题翻译：用于分离飞机辅助动力装置的飞机辅助动力装置悬架系统
公开(公告)号：US20110084192A1
公开(公告)日：2011-04-14
申请号：US12971156
申请日：2010-12-17
申请人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
发明人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
IPC分类号： B64D27/00 , F16M13/00 , B23P17/04
CPC分类号： B64D41/00 , B64D2041/002 , Y10T29/49826
摘要： The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.
摘要翻译：本发明提供一种具有与飞行器隔离的辅助动力单元的飞行器。辅助动力单元悬挂系统包括至少一个悬挂联动装置。悬挂连杆以第一低刚性弹性体杆端终止。低刚度弹性体杆端具有较低的弹簧刚度，飞机辅助动力单元悬架系统为飞机辅助动力单元提供悬挂的辅助动力装置固有频率，悬挂辅助动力装置的固有频率低于飞机辅助动力装置的运行频率。

4. 发明授权

US07878448B2 Aircraft auxiliary power unit suspension system for isolating an aircraft auxiliary power unit 有权
标题翻译：用于隔离飞机辅助动力装置的飞机辅助动力装置悬架系统
公开(公告)号：US07878448B2
公开(公告)日：2011-02-01
申请号：US11397208
申请日：2006-04-04
申请人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
发明人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
IPC分类号： B64D27/26
CPC分类号： B64D41/00 , B64D2041/002 , Y10T29/49826
摘要： The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.
摘要翻译：本发明提供一种具有与飞行器隔离的辅助动力单元的飞行器。辅助动力单元悬挂系统包括至少一个悬挂联动装置。悬挂连杆以第一低刚性弹性体杆端终止。低刚度弹性体杆端具有较低的弹簧刚度，飞机辅助动力单元悬架系统为飞机辅助动力单元提供悬挂的辅助动力装置固有频率，悬挂辅助动力装置的固有频率低于飞机辅助动力装置的运行频率。

5. 发明授权

US6065742A Multi-directional tuned vibration absorber 失效
标题翻译：多向调谐减振器
公开(公告)号：US6065742A
公开(公告)日：2000-05-23
申请号：US713384
申请日：1996-09-13
申请人： Gerald P. Whiteford
发明人： Gerald P. Whiteford
IPC分类号： F16F7/108 , F16F15/00 , F16M1/00
CPC分类号： F16F7/108
摘要： A Multi-Directional Tuned Vibration Absorber (MDTVA) (23) including a first tuning mass (32) vibrating at a first resonant frequency fn1 along a first axis, a second tuning mass (34) vibrating at the first resonant frequency along said first axis and also at a second resonant frequency fn2 along a second axis, a base member (21), a first spring (35) flexibly interconnected between the base member (21) and the first tuning mass (32), the first spring (35) substantially restricting motion of the first tuning mass (32) to motion along a first axis only, and a second spring (36) flexibly interconnected between the first tuning mass (32) and the second tuning mass (34), the second spring (36) substantially restricting relative motion between the first tuning mass (32) and second tuning mass (34), such that the relative motion of said second tuning mass (34) at said second frequency fn2 is along the second axis which is substantially perpendicular to the first axis. In another aspect, the first and second resonant frequencies fn1 and fn2 may be tuned independently by addition of wafer-like masses and/or adjustment of the position of the second tuning mass (34) and the MDTVA (23) can be used in a vehicle's isolation system.
摘要翻译：一种多向调谐振动吸收器（MDTVA）（23），包括沿着第一轴以第一谐振频率fn1振动的第一调谐质量块（32），沿着所述第一轴线以第一谐振频率振动的第二调谐质量块以及沿着第二轴的第二共振频率fn2，基部构件（21），在基部构件（21）和第一调谐块（32）之间挠曲地互连的第一弹簧（35），第一弹簧（35）基本上限制第一调谐质量块（32）的运动沿第一轴线运动，以及在第一调谐质量块（32）和第二调谐质量块（34）之间柔性互连的第二弹簧（36），第二弹簧）基本上限制第一调谐质量块（32）和第二调谐质量块（34）之间的相对运动，使得所述第二调谐质量块（34）在所述第二频率fn2处的相对运动是沿着基本上垂直于第二调谐质量块第一轴。在另一方面，第一和第二谐振频率fn1和fn2可以通过添加晶片状质量和/或调整第二调谐质量块（34）的位置来独立调谐，并且MDTVA（23）可以用于车辆隔离系统。

6. 发明申请

US20120018575A1 AIRCRAFT ENGINE MOUNTING SYSTEM AND METHOD OF MOUNTING AIRCRAFT ENGINES 有权
标题翻译：飞机发动机安装系统和安装飞机发动机的方法
公开(公告)号：US20120018575A1
公开(公告)日：2012-01-26
申请号：US13146286
申请日：2010-01-26
申请人： Gerald P. Whiteford , Daniel Zameroski
发明人： Gerald P. Whiteford , Daniel Zameroski
IPC分类号： B64D27/00 , B64D27/26 , B23P11/00
CPC分类号： B64D27/26 , B64D27/02 , B64D27/20 , B64D2027/262 , Y10T29/49826
摘要： In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine. The aircraft engine mounting system preferably includes a second engine attachment structure member (40), the airframe structure member second engine end (30) contained by the second engine attachment structure member, with the second engine attachment structure member having an outer engine mount member (42) grounded to the aircraft engine. The aircraft engine mounting system preferably includes the first engine attachment structure member and the second engine attachment structure member (40) grounded to the aircraft engine with a mounts spacing (MS) between the first engine
摘要翻译：在一个实施例中，本发明包括用于将飞机发动机安装到飞行器的飞机发动机安装系统（20）。飞机发动机安装系统优选地包括具有第一发动机端（28）和远端第二发动机端（30）的机身结构构件，其中在第一发动机端和远端第二发动机端之间具有飞机附件，用于接口的飞机附件所述机体结构构件具有飞机，所述机身结构构件具有从所述第一发动机端到所述远端第二发动机端的机身结构构件长度（YL）。飞机发动机安装系统优选地包括第一发动机安装结构构件（36），由第一发动机安装结构构件容纳的机身结构构件第一发动机端部（28），第一发动机安装结构构件具有外部发动机安装构件 38）接地到飞机发动机。飞机发动机安装系统优选地包括第二发动机安装结构构件（40），由第二发动机安装结构构件容纳的机身结构构件第二发动机端部（30），其中第二发动机安装结构构件具有外部发动机安装构件 42）接地到飞机发动机。飞机发动机安装系统优选地包括第一发动机附接结构构件和第二发动机附接结构构件（40），其在第一发动机之间以安装间隔（MS）接地到飞行器发动机

7. 发明授权

US06581874B2 Mounting assembly for an aircraft auxiliary power unit and method 有权
公开(公告)号：US06581874B2
公开(公告)日：2003-06-24
申请号：US09965942
申请日：2001-09-27
申请人： Jacques Lemire , Kirk W. Olsen , Francis J. DePriest , Thomas R. Law , Gerald P. Whiteford , Paul J. Bachmeyer
发明人： Jacques Lemire , Kirk W. Olsen , Francis J. DePriest , Thomas R. Law , Gerald P. Whiteford , Paul J. Bachmeyer
IPC分类号： B64D2700
CPC分类号： B64D41/00 , B64D2041/002
摘要： A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

8. 发明授权

US5957440A Active fluid mounting 失效
标题翻译：主动流体安装
公开(公告)号：US5957440A
公开(公告)日：1999-09-28
申请号：US835433
申请日：1997-04-08
申请人： Peter J. Jones , Douglas E. Ivers , Kevin C. Cooney , Gerald P. Whiteford
发明人： Peter J. Jones , Douglas E. Ivers , Kevin C. Cooney , Gerald P. Whiteford
IPC分类号： F16F7/10 , F16F13/06 , F16F13/22 , F16F13/26 , F16F5/00
CPC分类号： F16F13/22 , F16F13/06 , F16F13/26 , F16F7/1005 , F16F2228/00
摘要： An active fluid mounting for isolating vibration between a vibrating member (21) and a structure (23). In one aspect, the active fluid mounting (20) includes an inner member (22), an outer member (24), a first flexible element (26), and an cartridge-like active fluid element (28) which is unitary and readily detachable, attached between the inner and outer members, (22) and (24). The cartridge-like active fluid element (28) preferably includes a first housing member (30) for attachment to inner member (22), a second housing member (32) for attachment to outer member (24), a second flexible element (34) for flexibly interconnecting first housing member (30) to second housing member (32), at least one fluid chamber (36) having a volume stiffness, a fluid (40) contained within, a moveable piston (42) interacting with fluid (40) in the fluid chamber (36) to cause pressure variations and produce dynamic forces which act between the inner and outer member, (22) and (24), and a preferable coil-and-magnet assembly (44) for driving piston (42) housed internally within active fluid element (28). In another aspect, a piston (42a) which is inductively driven is described. In yet another, an interchangeable motor unit including a magnet (68), coil (70), and pole pieces (66) is received within the inner member (22).
摘要翻译：一种用于隔离振动构件（21）和结构（23）之间的振动的主动流体安装件。在一个方面，主动流体安装件（20）包括内部构件（22），外部构件（24），第一柔性元件（26）和总成并且容易地形成的筒状活性流体元件（28）可拆卸地安装在内部和外部构件（22）和（24）之间。盒状有源流体元件（28）优选地包括用于附接到内部构件（22）的第一壳体构件（30），用于附接到外部构件（24）的第二壳体构件（32），第二柔性元件（34），用于将第一壳体构件（30）柔性地互连到第二壳体构件（32），具有体积刚度的至少一个流体室（36），容纳在与流体（40）相互作用的可移动活塞（42）内的流体）导致流体室（36）中的压力变化并产生作用在内部和外部构件（22）和（24）之间的动力，以及用于驱动活塞（42）的优选的线圈和磁体组件（44））容纳在主动流体元件（28）内部。另一方面，描述了感应驱动的活塞（42a）。在另一方面，包括磁体（68），线圈（70）和极片（66）的可互换电动机单元被容纳在内部构件（22）内。

9. 发明授权

US09527598B2 Aircraft engine mounting system and method of mounting aircraft engines 有权
标题翻译：飞机发动机安装系统和安装飞机发动机的方法
公开(公告)号：US09527598B2
公开(公告)日：2016-12-27
申请号：US13146286
申请日：2010-01-26
申请人： Gerald P. Whiteford , Daniel Zameroski
发明人： Gerald P. Whiteford , Daniel Zameroski
IPC分类号： B64D27/26 , B64D27/20
CPC分类号： B64D27/26 , B64D27/02 , B64D27/20 , B64D2027/262 , Y10T29/49826
摘要： In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine. The aircraft engine mounting system preferably includes a second engine attachment structure member (40), the airframe structure member second engine end (30) contained by the second engine attachment structure member, with the second engine attachment structure member having an outer engine mount member (42) grounded to the aircraft engine. The aircraft engine mounting system preferably includes the first engine attachment structure member (36) and the second engine attachment structure member (40) grounded to the aircraft engine with a mounts spacing (MS) between the first engine.
摘要翻译：在一个实施例中，本发明包括用于将飞机发动机安装到飞行器的飞机发动机安装系统（20）。飞机发动机安装系统优选地包括具有第一发动机端（28）和远端第二发动机端（30）的机身结构构件，其中在第一发动机端和远端第二发动机端之间具有飞机附件，用于接口的飞机附件所述机体结构构件具有飞机，所述机身结构构件具有从所述第一发动机端到所述远端第二发动机端的机身结构构件长度（YL）。飞机发动机安装系统优选地包括第一发动机安装结构构件（36），由第一发动机安装结构构件容纳的机身结构构件第一发动机端部（28），第一发动机安装结构构件具有外部发动机安装构件 38）接地到飞机发动机。飞机发动机安装系统优选地包括第二发动机安装结构构件（40），由第二发动机安装结构构件容纳的机身结构构件第二发动机端部（30），其中第二发动机安装结构构件具有外部发动机安装构件 42）接地到飞机发动机。飞机发动机安装系统优选地包括第一发动机附接结构构件（36）和第二发动机附接结构构件（40），其在第一发动机之间以安装间距（MS）接地到飞机发动机。

10. 发明授权

US08413926B2 Aircraft auxiliary power unit suspension system for isolating an aircraft auxiliary power unit 有权
标题翻译：用于隔离飞机辅助动力装置的飞机辅助动力装置悬架系统
公开(公告)号：US08413926B2
公开(公告)日：2013-04-09
申请号：US12971156
申请日：2010-12-17
申请人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
发明人： Kirk W. Olsen , Gerald P. Whiteford , Pat Sheridan , Scott K. Thompson
IPC分类号： B64D27/00
CPC分类号： B64D41/00 , B64D2041/002 , Y10T29/49826
摘要： The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.
摘要翻译：本发明提供一种具有与飞行器隔离的辅助动力单元的飞行器。辅助动力单元悬挂系统包括至少一个悬挂联动装置。悬挂连杆以第一低刚性弹性体杆端终止。低刚度弹性体杆端具有较低的弹簧刚度，飞机辅助动力单元悬架系统为飞机辅助动力单元提供悬挂的辅助动力装置固有频率，悬挂辅助动力装置的固有频率低于飞机辅助动力装置的运行频率。

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