公开(公告)号：US20080145621A1

公开(公告)日：2008-06-19

申请号：US11953171

申请日：2007-12-10

申请人： Thomas Manfredotti

发明人： Thomas Manfredotti

IPC分类号： F16F15/12 ,  B32B3/12

CPC分类号： B64C1/40 ,  B64C27/001 ,  B64C2027/004 ,  F16F1/3737 ,  F16F1/377 ,  F16F3/12 ,  F16F15/085 ,  Y10T428/24322 ,  Y10T428/24661 ,  Y10T428/249965 ,  Y10T428/24998

摘要： The present invention relates to an absorbent covering (1) having high damping power, secured on a structure (2) and comprising a dissipater mesh made up of a plurality of dissipating elements (3) and of nodes (4) each having its bottom end (4′) secured on said structure (2). In remarkable manner, said bottom ends (4′) of said nodes (4) project from said dissipating elements (3) so as to leave an empty space (5) between the dissipating elements (3) and said structure (2), said absorbent covering (1) including main absorbent elements (6) arranged in said empty space (5), each of said main absorbent elements (6) being secured firstly to a bottom face (3′) of a said dissipating element (3) and secondly to said structure (2).

摘要翻译： 本发明涉及一种具有高阻尼功率的吸收性覆盖物（1），其固定在结构（2）上并且包括由多个耗散元件（3）和节点（4）构成的散射网，每个节点（4）的底端 （4'）固定在所述结构（2）上。 以显着的方式，所述节点（4）的所述底端（4'）从所述散热元件（3）伸出，以在散热元件（3）和所述结构（2）之间留下空的空间（5），所述 吸收性覆盖物（1），其包括设置在所述空空间（5）中的主要吸收元件（6），每个所述主吸收元件（6）首先被固定到所述散热元件（3）的底面（3'），并且 其次到所述结构（2）。

公开(公告)号：US07360994B2

公开(公告)日：2008-04-22

申请号：US11069987

申请日：2005-03-03

申请人： Elio Zoppitelli

发明人： Elio Zoppitelli

IPC分类号： B64C21/51

CPC分类号： B64C27/51 ,  B64C2027/004 ,  F16F9/535 ,  G05D19/02 ,  Y10S416/50

摘要： The present invention relates to a method of controlling a drag damper for a helicopter blade under all operating configurations of the helicopter, the method consisting in: a) measuring the elongation of the damper; b) amplifying the measured signal and filtering out noise; c) isolating the natural response of the blade corresponding to the drag movement of the blade from the forced response imposed by a rotor driving the blades; and d) analyzing in real time the natural response and adjusting the damping as a function of the analysis.

摘要翻译： 本发明涉及在直升机的所有操作构型下控制用于直升机叶片的减震器的方法，该方法包括：a）测量阻尼器的伸长率; b）放大测量信号并滤除噪声; c）分离与叶片的牵引运动对应的叶片的自然响应与驱动叶片的转子施加的强制响应; 和d）实时分析自然响应和调整阻尼作为分析的函数。

公开(公告)号：US20060255206A1

公开(公告)日：2006-11-16

申请号：US11406004

申请日：2006-04-18

申请人： Mark Jolly ,  Andrew Meyers

发明人： Mark Jolly ,  Andrew Meyers

IPC分类号： B64C13/16

CPC分类号： F16F7/1011 ,  B64C19/00 ,  B64C2027/004 ,  B64C2220/00

摘要： An aircraft with an aircraft elastic aerostructure body inflight aerodynamically initiated transient lateral modal bending response suppression system is provided. The aircraft elastic aerostructure body has an inflight aerodynamically initiated transient lateral modal bending response which is suppressed by the transient lateral modal bending response suppression system. The aircraft transient lateral modal bending response suppression system includes a sensor for sensing the inflight aerodynamically initiated transient lateral modal bending response and an electromagnetic moving mass shaker, the electromagnetic moving mass shaker having a moving mass and a mounting base, with the moving mass shaker mounted to the elastic aerostructure body with the mounting base. The system includes a controller wherein the first sensor outputs a sensed lateral modal bending response signal into the controller and the controller electromagnetically drives the electromagnetic moving mass shaker to suppress the lateral modal bending response.

摘要翻译： 提供一种具有飞机弹性航空结构体飞机空中动力学启动的瞬态侧向模态弯曲响应抑制系统的飞机。 飞机弹性航空结构体具有飞行空气动力学启动的瞬态横向模态弯曲响应，由瞬态侧向模态弯曲响应抑制系统抑制。 飞机瞬态横向模态弯曲响应抑制系统包括用于感测机动空气动力学启动的瞬时侧向模态弯曲响应的传感器和电磁移动质量振动器，电动移动质量振动器具有移动质量和安装基座，移动质量振动器安装 到具有安装基座的弹性气动结构体。 该系统包括控制器，其中第一传感器将感测到的侧向模态弯曲响应信号输出到控制器中，并且控制器电磁驱动电磁移动质量振动器以抑制侧向模态弯曲响应。

公开(公告)号：US20040248943A9

公开(公告)日：2004-12-09

申请号：US10191012

申请日：2002-07-08

申请人： Pharmacia Corporation

发明人： John J. Talley ,  James A. Sikorski ,  Matthew J. Graneto ,  Bryan H. Norman ,  Balekudru Devadas ,  Hwang-Fun Lu

IPC分类号： C07D277/30 ,  C07D275/02 ,  C07D263/34 ,  C07D261/06

CPC分类号： C07D231/12 ,  B60G17/018 ,  B60G2400/102 ,  B60G2400/206 ,  B60G2400/25 ,  B60G2400/60 ,  B60G2400/91 ,  B64C27/001 ,  B64C2027/004 ,  C07D263/32

摘要： This invention is in the field of antiinflammatory pharmaceutical agents and specifically relates to compounds, compositions and methods for treating disorders mediated by cyclooxygenase-2 or 5-lipoxygenase, such as inflammation.

摘要翻译： 本发明涉及抗炎药物领域，具体涉及用于治疗由环氧合酶-2或5-脂氧合酶如炎症介导的病症的化合物，组合物和方法。

公开(公告)号：US06671590B1

公开(公告)日：2003-12-30

申请号：US10139256

申请日：2002-04-30

申请人： Mark D. Betzina ,  Khanh Q. Nguyen

发明人： Mark D. Betzina ,  Khanh Q. Nguyen

IPC分类号： B64C100

CPC分类号： B64C27/001 ,  B64C2027/004

摘要： Methods and systems for reducing noise generated by rotating blades of a tiltrotor aircraft. A rotor-blade pitch angle associated with the tiltrotor aircraft can be controlled utilizing a swashplate connected to rotating blades of the tiltrotor aircraft. One or more Higher Harmonic Control (HHC) signals can be transmitted and input to a swashplate control actuator associated with the swashplate. A particular blade pitch oscillation (e.g., four cycles per revolution) is thereafter produced in a rotating frame of reference associated with the rotating blades in response to input of an HHC signal to the swashplate control actuator associated with the swashplate to thereby reduce noise associated with the rotating blades of the tiltrotor aircraft. The HHC signal can be transmitted and input to the swashplate control actuator to reduce noise of the tiltrotor aircraft in response to a user input utilizing an open-loop configuration.

摘要翻译： 用于降低旋转飞机旋转叶片产生噪音的方法和系统。 可以利用连接到倾斜旋转飞机的旋转叶片的斜盘来控制与倾斜旋转飞机相关联的转子叶片俯仰角。 一个或多个高级谐波控制（HHC）信号可被传输并输入到与斜盘相关联的斜盘控制致动器。 响应于将HHC信号输入到与斜盘相关联的斜盘控制致动器，从而在与旋转叶片相关的旋转参考系中产生特定叶片间距振荡（例如，每转四个周期），从而减少与 倾斜旋翼飞机的旋转叶片。 可以将HHC信号传输并输入到斜盘控制致动器，以便响应于利用开环配置的用户输入来降低倾斜旋翼飞机的噪音。

公开(公告)号：US06467723B1

公开(公告)日：2002-10-22

申请号：US09686009

申请日：2000-10-10

申请人： Dino J. Rossetti ,  Mark A. Norris ,  Guy D. Billoud

发明人： Dino J. Rossetti ,  Mark A. Norris ,  Guy D. Billoud

IPC分类号： B64D4700

CPC分类号： B64C27/001 ,  B64C2027/004

摘要： An aircraft has a fuselage that defines an interior cabin and an exterior; a first housing located along one side of the fuselage exterior; a second housing located along the second side of the fuselage exterior; and an active vibration control system for limiting fuselage vibration, the vibration control system comprising a plurality of sensors located in the cabin; a controller in signal receiving relation with the sensor means; first actuator means located in the first housing and second actuator means located in the second housing and wherein the actuator means are in signal receiving relation with the controller.

摘要翻译： 飞机具有定义内部舱室和外部的机身; 位于机身外部一侧的第一个外壳; 位于机身外部的第二侧的第二壳体; 以及用于限制机身振动的主动振动控制系统，所述振动控制系统包括位于所述舱室中的多个传感器; 与传感器装置的信号接收关系的控制器; 位于第一壳体中的第一致动器装置和位于第二壳体中的第二致动器装置，并且其中致动器装置与控制器处于信号接收关系。

公开(公告)号：US20020058810A1

公开(公告)日：2002-05-16

申请号：US09997633

申请日：2001-11-29

申请人： Pharmacia Corporation

发明人： John J. Talley ,  James A. Sikorski ,  Matthew J. Graneto ,  Jeffery S. Carter ,  Bryan H. Norman ,  Balekudru Devadas

IPC分类号： C07D43/04

CPC分类号： C07D231/12 ,  B60G17/018 ,  B60G2400/102 ,  B60G2400/206 ,  B60G2400/25 ,  B60G2400/60 ,  B60G2400/91 ,  B64C27/001 ,  B64C2027/004 ,  C07D263/32

摘要： This invention is in the field of antiinflammatory pharmaceutical agents and specifically relates to compounds, compositions and methods for treating disorders mediated by cyclooxygenase-2 or 5-lipoxygenase, such as inflammation.

摘要翻译： 本发明涉及抗炎药物领域，具体涉及用于治疗由环氧合酶-2或5-脂氧合酶如炎症介导的病症的化合物，组合物和方法。

公开(公告)号：US06224014B1

公开(公告)日：2001-05-01

申请号：US09164931

申请日：1998-10-01

申请人： Marc Dussac

发明人： Marc Dussac

IPC分类号： B64C2700

CPC分类号： B64C27/001 ,  B64C2027/002 ,  B64C2027/004 ,  G10K11/178 ,  G10K2210/1281 ,  G10K2210/129 ,  G10K2210/501

摘要： The present invention relates to a device for reducing the noise inside a rotary-wing aircraft, especially a helicopter. According to the invention, said device (1) comprises at least one sensor (Ca, Cb) for measuring the values of at least one vibrational and/or acoustic parameter representing a vibrational and/or acoustic effect of at least one source of noise, at least one mechanical means (A) that can be controlled and is capable of creating a force capable of reducing said vibrational and/or acoustic effect, and a control unit (UC) for controlling the mechanical means (A), on the basis of the values measured by the sensor (Ca, Cb).

摘要翻译： 本发明涉及一种用于减少旋转翼飞行器，特别是直升机内的噪声的装置。根据本发明，所述装置（1）包括至少一个传感器（Ca，Cb），用于测量至少一个 表示至少一个噪声源的振动和/或声音效应的振动和/或声学参数，能够被控制并能够产生能够减少所述振动和/或声学的力的至少一个机械装置（A） 效果以及用于根据由传感器（Ca，Cb）测量的值来控制机械装置（A）的控制单元（UC）。

公开(公告)号：US5456341A

公开(公告)日：1995-10-10

申请号：US52474

申请日：1993-04-23

申请人： Kenneth D. Garnjost ,  Christopher A. Rauch ,  Gonzalo J. Rey

发明人： Kenneth D. Garnjost ,  Christopher A. Rauch ,  Gonzalo J. Rey

IPC分类号： B64C27/51 ,  B60G17/018 ,  B64C27/00 ,  F16F7/10 ,  F16F15/02 ,  F16F15/03 ,  G05D19/02 ,  F16F15/04

CPC分类号： F16F7/1005 ,  B60G17/018 ,  B64C27/001 ,  F16F15/03 ,  B60G2202/25 ,  B60G2202/413 ,  B60G2202/422 ,  B60G2400/102 ,  B60G2400/206 ,  B60G2400/25 ,  B60G2400/60 ,  B60G2400/91 ,  B60G2600/182 ,  B64C2027/004 ,  B64C2027/005

摘要： An actively-controlled resonant-type force generator (20) is adapted to be attached to a structure (21), and includes a mass (23) mounted for movement relative to the structure and a plurality of springs (22, 24) operatively arranged between the mass and the structure. A servoactuator (26) is arranged to controllably excite the mass-spring system. The actual force (F.sub.a) transmitted from the mass to the structure is compared with a commanded force (F.sub.c) to produce a force error signal (F.sub.e). The actuator is caused to produce a velocity as a function of the error signal. The gain of the closed force loop is selected so that the resonance of the mass-spring system has an effective damping ratio (.zeta.) greater than about 0.5, and preferably about 0.7. Thus, the mass-spring system will not be substantially resonantly excited by vibrations of the structure near its resonant frequency (.omega..sub.n).

摘要翻译： 主动控制的共振型力发生器（20）适于附接到结构（21），并且包括安装成相对于结构移动的质量块（23）和可操作地布置的多个弹簧（22,24） 在质量和结构之间。 伺服致动器（26）布置成可控地激发质量弹簧系统。 将从质量传递到结构的实际力（Fa）与指令力（Fc）进行比较以产生力误差信号（Fe）。 使致动器产生作为误差信号的函数的速度。 选择闭合力回路的增益，使得质量弹簧系统的共振具有大于约0.5，优选约0.7的有效阻尼比（zeta）。 因此，质子弹簧系统将不会在其谐振频率（ωn）附近的结构的振动基本上共振地激发。

公开(公告)号：US5316240A

公开(公告)日：1994-05-31

申请号：US928306

申请日：1992-08-12

申请人： Laurent Girard ,  Tomasz Krysinski ,  Pierre Michel

发明人： Laurent Girard ,  Tomasz Krysinski ,  Pierre Michel

IPC分类号： B64C27/00 ,  F16F7/10 ,  F16F15/00 ,  F16F15/02 ,  B64C27/51 ,  F16F7/00

CPC分类号： B64C27/001 ,  F16F15/02 ,  F16F7/1017 ,  B64C2027/002 ,  B64C2027/004 ,  F16F2230/16

摘要： The present invention relates to a device for elastic linking between two parts (3, 5) in order to filter the vibratory excitations which are transmitted from one to the other, comprising:at least one linking element (7) between said parts (3, 5) comprising a transmission member (8) for the static force between said parts (3, 5), and an actuator (9) associated with said transmission member (8),at least one means of measurement (10) of a physical quantity which is representative of said vibratory excitations, and able to supply corresponding first signals, andelectronic processing means (12) for said first signals in order to convert them into second control signals for said actuator (9).According to the invention, said measurement means (10) is mounted on said linking element (7).

摘要翻译： 本发明涉及一种用于将两个部分（3,5）之间弹性连接的装置，以便将从一个传递到另一个的振动激励过滤，包括：至少一个连接元件（7） 5）包括用于所述部件（3,5）之间的静力的传动构件（8）和与所述传动构件（8）相关联的致动器（9），至少一个物理量测量装置（10） 其代表所述振动激励，并且能够提供对应的第一信号，以及用于所述第一信号的电子处理装置（12），以便将它们转换成用于所述致动器（9）的第二控制信号。 根据本发明，所述测量装置（10）安装在所述连接元件（7）上。