公开(公告)号：WO1996017339A1

公开(公告)日：1996-06-06

申请号：PCT/US1995014848

申请日：1995-11-14

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  HODGSON, Douglas, A. ,  JOLLY, Mark, R. ,  NORRIS, Mark, A. ,  ROSSETTI, Dino, J. ,  SWANSON, Douglas, A. ,  SOUTHWARD, Steve, C.

IPC: G10K11/178

CPC classification number: G10K11/178 ,  G10K2210/10 ,  G10K2210/103 ,  G10K2210/124 ,  G10K2210/3046 ,  G10K2210/3217 ,  G10K2210/512

Abstract: An active noise and vibration cancellation system with broadband control capability. A broadband disturbance signal detector (42, 42a) positioned within a closed compartment (41) 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 vibration energy source to a controller. The controller (46) receives the broadband disturbance signal (44) as well as error signals from error sensors (52) which, by virtue of adaptive filters within the controller, enhance the cancellation capability of the control signals produced by one or more actuators (50) positioned within the compartment.

Abstract translation: 具有宽带控制能力的主动噪声和振动消除系统。 位于诸如飞机机舱或车辆乘客室之类的封闭隔室（41）内的宽带扰动信号检测器（42,42a）提供了表示从振动能量源发出的宽带信号的频谱和对应的相对幅度的信号， 一个控制器 控制器（46）接收宽带干扰信号（44）以及来自误差传感器（52）的误差信号，由误差传感器（52）利用控制器内的自适应滤波器增强由一个或多个致动器产生的控制信号的消除能力 50）。

公开(公告)号：WO2005083626A2

公开(公告)日：2005-09-09

申请号：PCT/US2004/033848

申请日：2004-10-14

Applicant: LORD CORPORATION ,  SOUTHWARD, Steve, C. ,  JOLLY, Mark, R. ,  FERGUSON, Matthew, K. ,  FOWLER, Leslie, P.

Inventor： LORD CORPORATION ,  SOUTHWARD, Steve, C. ,  JOLLY, Mark, R. ,  FERGUSON, Matthew, K. ,  FOWLER, Leslie, P.

IPC: G06K9/00

CPC classification number: G01B7/023 ,  G01D5/485 ,  G01R29/02 ,  G04F10/00

Abstract: A magnetostrictive sensor system and a method of measuring a magnetostrictive sensor pulse is provided. The measurement system and method includes providing a digital buffer circuit connected with an analog to digital converter to a an analog waveform detector for receiving a magnetostrictive pulse waveform from a magnetostrictive waveguide. A template waveform is provided, and a returned magnetostrictive pulse waveform is received into the digital buffer circuit. The received pulse waveform is compared with the template waveform to determine an arrival time of the returned magnetostrictive pulse waveform. Providing the template waveform includes providing a synthesized return waveform generated to simulate a characteristic magnetostrictive return pulse waveform of the magnetostrictive system. The magnetostrictive sensor system includes a magnetostrictive waveguide, an analog waveform detector for receiving a magnetostrictive pulse waveform from the magnetostrictive waveguide, a comparing correlating processor with a template waveform for comparing the received magnetostrictive pulse waveform with the template waveform to determine an arrival time of the returned magnetostrictive pulse waveform.

Abstract translation: 提供了一种磁致伸缩传感器系统和一种测量磁致伸缩传感器脉冲的方法。 测量系统和方法包括提供与模数转换器连接的数字缓冲电路到模拟波形检测器，用于从磁致伸缩波导接收磁致伸缩脉冲波形。 提供模板波形，并且返回的磁致伸缩脉冲波形被接收到数字缓冲器电路中。 将接收到的脉冲波形与模板波形进行比较，以确定返回的磁致伸缩脉冲波形的到达时间。 提供模板波形包括提供生成的用于模拟磁致伸缩系统的特征磁致伸缩返回脉冲波形的合成返回波形。 磁致伸缩传感器系统包括磁致伸缩波导，用于从磁致伸缩波导接收磁致伸缩脉冲波形的模拟波形检测器，用于将接收的磁致伸缩脉冲波形与模板波形进行比较的模板波形的比较相关处理器，以确定 返回磁致伸缩脉冲波形。

公开(公告)号：WO1995034769A1

公开(公告)日：1995-12-21

申请号：PCT/US1995007474

申请日：1995-06-12

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  SOUTHWARD, Steve, C. ,  IVERS, Douglas, E.

IPC: F16F15/00

CPC classification number: F16F13/08 ,  F16F1/40 ,  F16F7/1005 ,  F16F15/00 ,  F16F15/027 ,  F16F15/08 ,  G10K11/17857 ,  G10K11/17883 ,  G10K2210/107 ,  G10K2210/121 ,  G10K2210/123 ,  G10K2210/1281 ,  G10K2210/129 ,  G10K2210/3016 ,  G10K2210/321

Abstract: An active mount (10) for fixed wing applications. One aspect of the invention provides decoupling of two tones which are close in frequency by positioning the mount actuators (16) and error sensors (18) in the primary transmission path of the disturbance vibration and by providing adequate spatial separation between the two sets of error sensors to reduce or eliminate cross-coupling of the signals. Another aspect of the invention utilizes orthogonally positioned actuators (16) with corresponding actuators of paired mounts being focalized for each engine (17, 19).

Abstract translation: 用于固定翼应用的主动安装座（10）。 本发明的一个方面通过将安装致动器（16）和误差传感器（18）定位在干扰振动的主传动路径中并通过在两组误差之间提供足够的空间间隔来提供频率接近的两个音调的去耦 传感器来减少或消除信号的交叉耦合。 本发明的另一方面利用正交定位的致动器（16），其中对于每个发动机（17,19）对成对安装件的相应致动器进行调焦。

公开(公告)号：WO2003091658A1

公开(公告)日：2003-11-06

申请号：PCT/US2003/012837

申请日：2003-04-23

Applicant: LORD CORPORATION

Inventor： ALTIERI, Russell, E. ,  KUHN, James, F. ,  JOLLY, Mark, R. ,  SOUTHWARD, Steve, C. ,  BADRE-ALAM, Askari ,  FOWLER, Leslie, P.

IPC: G01B7/31

CPC classification number: G01B7/31 ,  B64C29/0025 ,  B64F5/60

Abstract: Methods and systems for monitoring rotating shaft shafts (28) and couplings (30) in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling (30) in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings (30) are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors (40) to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components (36) of the propulsion system drive shaft. The relative position of the sensors (40) is rigidly fixed externally from the rotating targets (36) with a structural frame. The collar misalignment measuring system of the invention provide a misalignment measurement of the propulsion system drive shaft flexible coupling (30) which relates to a critical performance of rotating shaft coupling (30) in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling (30) in a fixed wing aircraft propulsion system.

Abstract translation: 描述了用于监测飞机推进系统中的旋转轴轴（28）和联轴器（30）的方法和系统。 测量系统/方法提供了对固定翼飞行器车辆推进系统中的旋转轴柔性联轴器（30）的准确和精确的监测。 测量系统/方法提供了一种高可靠性的短距离垂直着陆固定翼飞机，其中垂直推进动态旋转驱动轴系统和联轴器（30）被实时监控。 车轴联轴器未对准测量系统利用多个位置传感器（40）来提供对推进系统驱动轴的旋转传感器目标部件（36）的动态特性的高度可靠和精确的确定。 传感器（40）的相对位置通过结构框架从旋转靶（36）的外部刚性固定。 本发明的套环未对准测量系统提供了推进系统驱动轴柔性联轴器（30）的未对准测量，其涉及在飞行器车辆的操作中旋转轴联轴器（30）的关键性能。 该方法/系统提供用于监测旋转驱动轴系统并动态地测量固定翼飞机推进系统中的旋转驱动轴联轴器（30）。

公开(公告)号：WO1996017340A1

公开(公告)日：1996-06-06

申请号：PCT/US1995014852

申请日：1995-11-14

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  JOLLY, Mark, R. ,  NORRIS, Mark, A. ,  ROSSETTI, Dino, J. ,  SWANSON, Douglas, A. ,  SOUTHWARD, Steve, C.

IPC: G10K11/178

CPC classification number: G10K11/178 ,  G10K2210/128 ,  G10K2210/3027 ,  G10K2210/3028 ,  G10K2210/3046 ,  G10K2210/509 ,  G10K2210/51 ,  G10K2210/512

Abstract: Actuators (19L, 19H) for active vibrational energy control systems are frequency focused. The high-frequency cancellation function is decoupled (18L, 18H) from the low-frequency cancellation function to enable the size, force, number and placement of the actuators to be optimized. A hybrid system (not represented) employing structural actuators to cancel low-frequency vibrations and speakers to cancel higher-frequency vibrations is also taught.

Abstract translation: 用于主动振动能量控制系统的致动器（19L，19H）是频率集中的。 高频消除功能与低频消除功能解耦（18L，18H），使得执行器的尺寸，力，数量和布局得以优化。 还教导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（未示出）。

公开(公告)号：WO1996014634A1

公开(公告)日：1996-05-17

申请号：PCT/US1995013453

申请日：1995-10-19

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  SOUTHWARD, Steve, C. ,  MILLER, Lane, R.

IPC: G10K11/178

CPC classification number: H03H21/0012 ,  G10K11/178 ,  G10K2210/3011 ,  G10K2210/3017 ,  G10K2210/3026 ,  G10K2210/3027 ,  G10K2210/3031 ,  G10K2210/3032 ,  G10K2210/3042 ,  G10K2210/3049 ,  G10K2210/3053 ,  G10K2210/3054

Abstract: An active control method and apparatus for controlling vibration or sound wherein the computational burden to adaptively update the control filter within the update model is reduced. The apparatus includes means (not represented) for producing an input signal (36) for input to the update model (22) and the reduction block (26), means (not represented) for generating an error signal (41), and an output device (25) for canceling sound and/or vibration at a selected location. The method uses a gradient descent algorithm such as the filtered-x LMS algorithm and replaces the long filter model (23, 24) with a shortened length filter model (28, 30, 30'). Error signal information together with the output information from the shortened length filter model are used to update the coefficients of the control filter (32) according to an update calculation method. The shortened filter model only contains frequency response information at the L frequencies of interest. Because of the reduced amount of information contained in the shortened filter model, more updates per unit of time can be performed on the control filter(s) or a smaller or fewer processors or CPU's may be utilized. The method has applicability to feed-forward and feed-back type systems and also to systems using a waveform generator for supplying the input signal. The reduction method may be implemented on-line or off-line.

Abstract translation: 一种用于控制振动或声音的主动控制方法和装置，其中减少了在更新模型内自适应地更新控制滤波器的计算负担。 该装置包括用于产生用于输入到更新模型（22）和减少块（26）的输入信号（36）的装置（未示出），用于产生误差信号（41）的装置（未表示）和输出 用于在选定位置消除声音和/或振动的装置（25）。 该方法使用梯度下降算法，如过滤x LMS算法，并用缩短的长度过滤器模型（28,30,30'）替换长过滤器模型（23,24）。 误差信号信息与来自缩短的长度滤波器模型的输出信息一起用于根据更新计算方法来更新控制滤波器（32）的系数。 缩短的滤波器模型仅包含感兴趣的L个频率的频率响应信息。 由于缩短的过滤器模型中包含的信息量减少，因此可以在控制过滤器上执行每单位时间更多的更新，或者可以使用更小或更少的处理器或CPU。 该方法适用于前馈和反馈型系统，并且还适用于使用波形发生器提供输入信号的系统。 还原方法可以在线或离线实现。

公开(公告)号：WO2005022102A3

公开(公告)日：2005-03-10

申请号：PCT/US2004/028120

申请日：2004-08-27

Applicant: LORD CORPORATION ,  SOUTHWARD, Steve, C.

Inventor： SOUTHWARD, Steve, C.

IPC: G01L3/04

Abstract: The invention provides a method/system for measuring torque. The method/system includes providing a first rotating disk A having a target pattern and providing a second rotating disk 13 having a target pattern. The method/system includes providing a first set of at least three sensors, comprised of a first disk first sensor (1 A), a first disk second sensor (2A), and a first disk third sensor (3A), the first set of at least three sensors for sensing the first rotating disk target pattern with the first set of at least three sensors fixed around and encompassing the first rotating disk. The method/system includes providing a second set of at least three sensors, comprised of a second disk first sensor (lB), a second disk second sensor (2B), and a second disk third sensor (3B), the second set of at least three sensors for sensing the second rotating disk target pattern, with the second set of at least three sensors fixed around and encompassing the second rotating disk. The method/system includes measuring an apparent twist of the first rotating disk relative to the second rotating disk with the first set of at least three sensors and the second set of at least three sensors, and determining an actual twist angle from the measured apparent twist.

公开(公告)号：WO2005019030A2

公开(公告)日：2005-03-03

申请号：PCT/US2004/007331

申请日：2004-03-10

Applicant: LORD CORPORATION

Inventor： ALTIERI, Russell, E. ,  KUHN, James, F. ,  JOLLY, Mark, R. ,  SOUTHWARD, Steve, C. ,  BADRE-ALAM, Askari ,  FOWLER, Leslie, P.

IPC: B64D

CPC classification number: G01B7/31 ,  B64C29/005 ,  B64F5/60

Abstract: Methods and systems for monitoring rotating shafts and couplings in an aircraft vehicle propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vehicle’s dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The misalignment measuring system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system.

Abstract translation: 描述了用于监视飞行器车辆推进系统中的旋转轴和联轴器的方法和系统。 测量系统/方法可以精确和精确地监测固定翼飞机车辆推进系统中的旋转轴柔性联轴器。 测量系统/方法提供了一种高可靠性的短距离垂直着陆固定翼飞机，其中车辆的动态旋转驱动轴系统和联轴器被实时监控。 车轴联轴器未对准测量系统利用多个位置传感器来提供推进系统驱动轴的旋转传感器目标部件的动态特性的高度可靠和精确的确定。 传感器的相对位置通过结构框架从旋转目标的外部刚性固定。 不对准测量系统驱动轴柔性联轴器涉及飞机车辆操作中旋转轴联轴器的关键性能。 该方法/系统提供用于监视旋转驱动轴系统并动态地测量固定翼飞机推进系统中的旋转驱动轴联轴器。

公开(公告)号：WO2004094954A2

公开(公告)日：2004-11-04

申请号：PCT/US2004/012477

申请日：2004-04-21

Applicant: LORD CORPORATION

Inventor： ALTIERI, Russell, E. ,  KUHN, James, F. ,  JOLLY, Mark, R. ,  SOUTHWARD, Steve, C. ,  BADRE-ALAM, Askari ,  FOWLER, Leslie, P.

IPC: G01D

CPC classification number: G01B7/31 ,  B64C29/005 ,  B64F5/60

Abstract: Methods and systems for monitoring rotating shafts and couplings in an aircraft vehicle propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vehicle's dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The misalignment measuring system provides a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system.

Abstract translation: 描述了用于监视飞行器车辆推进系统中的旋转轴和联轴器的方法和系统。 测量系统/方法可以精确和精确地监测固定翼飞机车辆推进系统中的旋转轴柔性联轴器。 测量系统/方法提供了一种高可靠性的短距离垂直着陆固定翼飞机，其中车辆的动态旋转驱动轴系统和联轴器被实时监控。 车轴联轴器未对准测量系统利用多个位置传感器来提供推进系统驱动轴的旋转传感器目标部件的动态特性的高度可靠和精确的确定。 传感器的相对位置通过结构框架从旋转目标的外部刚性固定。 不对准测量系统提供了推进系统驱动轴柔性联轴器的不对准测量，其涉及在飞行器车辆的操作中旋转轴联轴器的关键性能。 该方法/系统提供用于监视旋转驱动轴系统并动态地测量固定翼飞机推进系统中的旋转驱动轴联轴器。

公开(公告)号：WO1998006089A1

公开(公告)日：1998-02-12

申请号：PCT/US1997011856

申请日：1997-07-07

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  ROSSETTI, Dino, J. ,  IVERS, Douglas, E. ,  NORRIS, Mark, A. ,  HEATH, Michael, C. ,  SOUTHWARD, Steve, C.

IPC: G10K11/178

CPC classification number: G10K11/17883 ,  G10K11/17854 ,  G10K11/17857 ,  G10K2210/121 ,  G10K2210/1281 ,  G10K2210/129 ,  G10K2210/3026 ,  G10K2210/3027 ,  G10K2210/3051 ,  G10K2210/3211 ,  G10K2210/501

Abstract: An Active Structural Control (ASC) system (10) and method which includes a plurality of Active Vibration Absorbers (AVAs) (40) attached to a yoke (32) included within a pylon structure (28) preferably comprising a spar (38) and a yoke (32) which is located intermediate between an aircraft fuselage (20) and an aircraft engine (18) for controlling acoustic noise and/or vibration generated within the aircraft's cabin (44) due to unbalances in the aircraft engine (18). The ASC system (10) includes a plurality of error sensors (42 or 63) for providing error signals, and at least one reference sensor (49 or 50) for providing reference signals indicative of the N1 and/or N2 engine rotations and/or vibrations, and a preferably digital electronic controller (46) for processing the error and reference signal information to provide output signals to dynamically vibrate the plurality of AVAs (40) attached to the yoke (32). The AVAs (40) preferably act in a radial, tangential, or fore and aft directions and may be located at the terminalend and/or at the base portion of the yoke (32). Further, the AVAs (40) may be Single Degree Of Freedom (SDOF) or Multiple Degree Of Freedom (MDOF) and may be tuned to have a passive resonance which substantially coincides with the N1 and/or N2 engine rotation and/or vibrations. In another aspect, reference signal processing is described which includes a modulo counter, a lookup table, and a digital IO device.

Abstract translation: 一种主动结构控制（ASC）系统（10）和方法，其包括附接到包括在塔结构（28）内的轭架（32）的多个主动减振器（AVAs）（40），优选地包括翼梁（38）和 位于飞行器机身（20）和飞机发动机（18）之间的轭架（32），用于控制由于飞行器引擎（18）中的不平衡而在飞机机舱（44）内产生的声音噪声和/或振动。 ASC系统（10）包括用于提供误差信号的多个误差传感器（42或63），以及用于提供指示N1和/或N2发动机旋转的参考信号的至少一个参考传感器（49或50）和/或 振动和优选数字电子控制器（46），用于处理误差和参考信号信息以提供输出信号以动态地振动附接到轭架（32）的多个AVA（40）。 AVA（40）优选地以径向，切向或前后方向作用，并且可以位于轭架（32）的末端和/或基座部分处。 此外，AVA（40）可以是单自由度（SDOF）或多自由度（MDOF），并且可以被调谐为具有与N1和/或N2发动机旋转和/或振动基本一致的无源共振。 在另一方面，描述了包括模计数器，查找表和数字IO设备的参考信号处理。