专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07571876B2 Aircraft landing gear assembly shimmy damper 有权
标题翻译：飞机起落架组件摆动阻尼器
公开(公告)号：US07571876B2
公开(公告)日：2009-08-11
申请号：US11375945
申请日：2006-03-15
申请人： Paul Joseph Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
发明人： Paul Joseph Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
IPC分类号： B64C25/00 , F16F1/00
CPC分类号： B64C25/505 , F16F7/02 , F16F2224/025
摘要： An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.
摘要翻译：提供了一种飞行器车辆组件，其包括具有内轴向中心孔的非弹性外管状构件，其具有连接的平滑内表面段的管状圆柱形摩擦界面和具有外接合表面段的非弹性内构件。非弹性内部构件被旋转地容纳在外部构件内部轴向中心孔中，其中非弹性内支柱构件可在所述外部构件内旋转。组件包括包围非弹性内支柱构件外接合表面段的弹性体。弹性体具有内接合表面段和外槽弹性体表面，内接合表面段结合到非弹性内构件外接合表面段。组件包括设置在外弹性体表面和非弹性外部构件摩擦接口内表面段之间的润滑脂，其中润滑的带槽的外弹性体表面接合非弹性外构件摩擦接口内表面段并阻止摆动旋转。

2. 发明授权

US5754662A Frequency-focused actuators for active vibrational energy control systems 失效
标题翻译：用于主动振动能量控制系统的频率聚焦执行器
公开(公告)号：US5754662A
公开(公告)日：1998-05-19
申请号：US347521
申请日：1994-11-30
申请人： Mark R. Jolly , Mark A. Norris , Dino J. Rossetti , Douglas A. Swanson , Steve C. Southward
发明人： Mark R. Jolly , Mark A. Norris , Dino J. Rossetti , Douglas A. Swanson , Steve C. Southward
IPC分类号： G10K11/178 , H03B29/00 , A61F11/06
CPC分类号： G10K11/1786 , G10K2210/128 , G10K2210/3027 , G10K2210/3028 , G10K2210/3046 , G10K2210/509 , G10K2210/51 , G10K2210/512
摘要： Actuators for active vibrational energy control systems which are frequency focused. The high-frequency cancellation function is decoupled from the low-frequency cancellation function to enable the size, force, number and placement of the actuators to be optimized. A hybrid system employing structural actuators to cancel low-frequency vibrations and speakers to cancel higher-frequency vibrations is also taught.
摘要翻译：主动振动能量控制系统的执行器是频率集中的。高频消除功能与低频消除功能解耦，使得执行器的尺寸，力，数量和布局得以优化。还教授了采用结构致动器来消除低频振动和扬声器以消除更高频率振动的混合系统。

3. 发明授权

US5526292A Broadband noise and vibration reduction 失效
标题翻译：宽带噪声和减振
公开(公告)号：US5526292A
公开(公告)日：1996-06-11
申请号：US347523
申请日：1994-11-30
申请人： Douglas A. Hodgson , Mark R. Jolly , Mark A. Norris , Dino J. Rossetti , Douglas A. Swanson , Steve C. Southward
发明人： Douglas A. Hodgson , Mark R. Jolly , Mark A. Norris , Dino J. Rossetti , Douglas A. Swanson , Steve C. Southward
IPC分类号： G10K11/178 , G10K11/16
CPC分类号： G10K11/1788 , G10K2210/10 , G10K2210/103 , G10K2210/124 , G10K2210/3046 , G10K2210/3217 , G10K2210/512
摘要： An active noise and vibration cancellation system with broadband control capability. A broadband disturbance signal detector positioned within a closed compartment such as an aircraft cabin or vehicle passenger compartment provides a signal representative of the frequency spectrum and corresponding relative magnitude of a broadband signal emanating from a vibrational energy source to a controller. The controller receives the broadband disturbance signal as well as error signals from error sensors which, by virtue of adaptive filters within the controller, enhance the cancellation capability of the control signals produced by one or more actuators positioned within the compartment.
摘要翻译：具有宽带控制能力的主动噪声和振动消除系统。定位在诸如飞机机舱或车辆乘客舱之类的封闭隔间内的宽带扰动信号检测器提供表示从振动能量源向控制器发出的宽带信号的频谱和对应的相对幅度的信号。控制器接收宽带干扰信号以及来自误差传感器的误差信号，该误差传感器借助于控制器内的自适应滤波器来增强由位于隔室内的一个或多个致动器产生的控制信号的消除能力。

4. 发明申请

US20120136533A1 HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS 有权
标题翻译：直升机振动控制系统和消除振动的循环发电系统
公开(公告)号：US20120136533A1
公开(公告)日：2012-05-31
申请号：US12971026
申请日：2010-12-17
申请人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
发明人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
IPC分类号： G06F19/00 , G05D15/00 , B64C27/473 , G05D19/00 , F16F7/00 , F16F7/10
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.
摘要翻译：一种包括车辆振动控制系统的旋翼飞机。车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少至少第一非旋转体圆周力产生器，至少第一非旋转体圆周力产生器，其与所述非旋转体固定连接，所述至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，主体圆形力发生器被控制以产生具有可控旋转力量级和可控旋转力相位的旋转力，可控旋转力量值从最小力量控制到最大力量值，并且可控旋转力相位被控制在参考旋转翼型飞行器构件传感器数据与旋转的旋转翼型轮毂相对于非旋转体相对旋转，其中由至少第一非旋转体振动传感器感测的振动减小。

5. 发明申请

US20090294583A1 AIRCRAFT LANDING GEAR ASSEMBLY SHIMMY DAMPER 有权
标题翻译：飞机起落架装配减震器
公开(公告)号：US20090294583A1
公开(公告)日：2009-12-03
申请号：US12538241
申请日：2009-08-10
申请人： Paul Joseph Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
发明人： Paul Joseph Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
IPC分类号： B64C25/50
CPC分类号： B64C25/505 , F16F7/02 , F16F2224/025
摘要： An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.
摘要翻译：提供了一种飞行器车辆组件，其包括具有内轴向中心孔的非弹性外管状构件，其具有连接的平滑内表面段的管状圆柱形摩擦界面和具有外接合表面段的非弹性内构件。非弹性内部构件被旋转地容纳在外部构件内部轴向中心孔中，其中非弹性内支柱构件可在所述外部构件内旋转。组件包括包围非弹性内支柱构件外接合表面段的弹性体。弹性体具有内接合表面段和外槽弹性体表面，内接合表面段结合到非弹性内构件外接合表面段。组件包括设置在外弹性体表面和非弹性外部构件摩擦界面内表面段之间的润滑脂，其中润滑的槽外弹性体表面接合非弹性外构件摩擦界面内表面段并且阻止摆动旋转。

6. 发明授权

US08534600B2 Aircraft landing gear assembly shimmy damper 有权
公开(公告)号：US08534600B2
公开(公告)日：2013-09-17
申请号：US12538241
申请日：2009-08-10
申请人： Paul J. Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
发明人： Paul J. Bachmeyer , Douglas A. Swanson , Bryan J. Pittman , Scott K. Thompson , Doug A. Hodgson
IPC分类号： B64C25/00 , F16F1/00
CPC分类号： B64C25/505 , F16F7/02 , F16F2224/025
摘要： An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.

7. 发明申请

US20100034655A1 HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS 有权
公开(公告)号：US20100034655A1
公开(公告)日：2010-02-11
申请号：US12419775
申请日：2009-04-07
申请人： Mark R. JOLLY , Andrew D. MEYERS , Daniel MELLINGER , Douglas E. IVERS , Askari BADRE-ALAM , Douglas A. SWANSON , Russell E. ALTIERI
发明人： Mark R. JOLLY , Andrew D. MEYERS , Daniel MELLINGER , Douglas E. IVERS , Askari BADRE-ALAM , Douglas A. SWANSON , Russell E. ALTIERI
IPC分类号： B64C27/32 , B63H3/08
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, a distributed force generation data communications network link, the distributed force generation data communications system network link linking together at least the first nonrotating body circular force generator and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the first nonrotating body circular force generator communicate force generation vibration control data through the distributed force generation data communications network, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hubrotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

8. 发明申请

US20090152396A1 Aircraft Landing Gear Assembly Shimmy Damper 有权
标题翻译：飞机起落架组件Shimmy阻尼器
公开(公告)号：US20090152396A1
公开(公告)日：2009-06-18
申请号：US11956118
申请日：2007-12-13
申请人： Paul Joseph BACHMEYER , Douglas A. SWANSON , Bryan J. PITTMAN , Scott K. THOMPSON , Doug HODGSON , Darrin M. JONES , Nicholas V. ANDERSON
发明人： Paul Joseph BACHMEYER , Douglas A. SWANSON , Bryan J. PITTMAN , Scott K. THOMPSON , Doug HODGSON , Darrin M. JONES , Nicholas V. ANDERSON
IPC分类号： B64C25/50
CPC分类号： B64C25/505 , F16F7/02 , F16F2224/025
摘要： An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. An elastomer encompasses the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment.
摘要翻译：提供了一种飞行器车辆组件，其包括具有内轴向中心孔的非弹性外管状构件，其具有连接的平滑内表面段的管状圆柱形摩擦界面和具有外接合表面段的非弹性内构件。非弹性内部构件被旋转地容纳在外部构件内部轴向中心孔中，其中非弹性内支柱构件可在所述外部构件内旋转。弹性体包括非弹性内支柱构件外接合表面段。弹性体具有内接合表面段和外槽弹性体表面，内接合表面段结合到非弹性内构件外接合表面段。

9. 发明授权

US5947457A Fluid-filled active vibration absorber 失效
标题翻译：流体填充主动减震器
公开(公告)号：US5947457A
公开(公告)日：1999-09-07
申请号：US835436
申请日：1997-04-08
申请人： Douglas A. Swanson , Peter J. Jones , Douglas E. Ivers , Kevin C. Cooney
发明人： Douglas A. Swanson , Peter J. Jones , Douglas E. Ivers , Kevin C. Cooney
IPC分类号： F16F7/10 , F16F13/22 , F16F13/26 , F16F5/00
CPC分类号： F16F13/264 , F16F13/22 , F16F7/10
摘要： A fluid-filled Active Vibration Absorber (AVA) (20) is described for attaching to, and controlling dynamic vibration of the member (22). The AVA (20) is comprised of primary tuning mass (23) preferably including an additional inertial tuning mass (26) which is associated with a primary resonant frequency (fn1), a flexible element (28) for interconnecting the primary mass (23) and, thus, interconnecting inertial tuning mass (26) to member (22), at least one, and preferably two, fluid chambers, (30) and (32), each having a defined volume stiffness Kv'1, Kv'2, a fluid (34) contained within the at least one and preferably two, fluid chambers, (30) and (32), a moveable piston (36) dynamically interacting with the fluid (34) in the at least one fluid chamber and preferably, in first and second fluid chambers, (30) and (32), to cause pressure variations which dynamically drive the primary tuning mass (23) within a range about the primary resonant frequency (fn1). Preferably, a coil (40) and magnet-and-pole assembly (38) driving the piston (36). The AVA (20) preferably includes a secondary resonance (fn2) which is tunable by adjusting the mass of the piston (36), volume stiffness Kv'1 of the first fluid chambers (30), and a piston area Ap1, amongst other parameters.
摘要翻译：描述了流体填充的主动减振器（AVA）（20），用于附接到并控制构件（22）的动态振动。 AVA（20）由初级调谐质量（23）组成，优选地包括与初级共振频率（fn1）相关联的附加惯性调谐质量块（26），用于使主质量（23）互连的柔性元件（28）并且因此将惯性调节质量（26）与构件（22），至少一个，优选两个流体室（30）和（32）相互连接，每个具有限定的体积刚度Kv'1，Kv'2，包含在所述至少一个且优选两个流体室（30）和（32）内的流体（34），与所述至少一个流体室中的流体（34）动态相互作用的可移动活塞（36）在第一和第二流体室（30）和（32）中，引起在围绕初级谐振频率（fn1）的范围内动态驱动初级调谐质量（23）的压力变化。优选地，驱动活塞（36）的线圈（40）和磁极组件（38）。 AVA（20）优选地包括通过调节活塞（36）的质量，第一流体室（30）的体积刚度Kv'1和活塞区域Ap1可调谐的次级共振（fn2），以及其他参数。

10. 发明授权

US09073627B2 Helicopter vibration control system and circular force generation systems for canceling vibrations 有权
标题翻译：直升机振动控制系统和用于消除振动的圆形力产生系统
公开(公告)号：US09073627B2
公开(公告)日：2015-07-07
申请号：US12971026
申请日：2010-12-17
申请人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
发明人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
IPC分类号： G06F19/00 , G05D15/00 , G05D19/00 , B64C27/00 , F16F15/22
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.
摘要翻译：一种包括车辆振动控制系统的旋翼飞机。车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少至少第一非旋转体圆周力产生器，至少第一非旋转体圆周力产生器，其与所述非旋转体固定连接，所述至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，主体圆形力发生器被控制以产生具有可控旋转力量级和可控旋转力相位的旋转力，可控旋转力量值从最小力量控制到最大力量值，并且可控旋转力相位被控制在参考旋转翼型飞行器构件传感器数据与旋转的旋转翼型轮毂相对于非旋转体相对旋转，其中由至少第一非旋转体振动传感器感测的振动减小。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式