公开(公告)号：WO2016099305A1

公开(公告)日：2016-06-23

申请号：PCT/PL2014/000150

申请日：2014-12-19

Applicant: GENERAL ELECTRIC COMPANY ,  NAGORSKI, Arkadiusz, Bartlomiej

Inventor： NAGORSKI, Arkadiusz, Bartlomiej ,  WATSON, Eric, Tracy ,  FUNG, Eric ,  NGUYEN, Quoc, Hoai

IPC: F01N1/06 ,  G10K11/178

CPC classification number: F01N1/065 ,  F01N2590/10 ,  F02C7/045 ,  G10K11/178 ,  G10K11/17857 ,  G10K11/17873 ,  G10K2210/1281 ,  G10K2210/3055 ,  G10K2210/3212 ,  G10K2210/3214

Abstract: A system includes an Active Noise Control (ANC) module unit configured to be installed within an air intake or exhaust of a power generation unit. The ANC module unit includes an ANC housing shaped to fit within the air intake or exhaust, an ANC core configured to be secured within the ANC housing, which includes a microphone configured to detect a sound generated by the power generation unit, a control board configured to control the noise-canceling sound based on the sound signal from the microphone and a set of pre-determined noise reduction transfer functions, and a first speaker configured to deliver a first noise-canceling sound to the air intake or exhaust.

Abstract translation: 一种系统包括被配置为安装在发电单元的进气或排气内的主动噪声控制（ANC）模块单元。 ANC模块单元包括成形为适合进气或排气的ANC壳体，被配置为固定在ANC壳体内的ANC芯，其包括配置成检测由发电单元产生的声音的麦克风，配置成 以基于来自麦克风的声音信号和一组预先确定的降噪传递功能来控制噪声消除声音，以及第一扬声器，被配置为将第一噪声消除声音传送到进气口或排气口。

公开(公告)号：WO2004027751A1

公开(公告)日：2004-04-01

申请号：PCT/RU2003/000234

申请日：2003-05-26

IPC: G10K11/178

CPC classification number: G10K11/178 ,  G10K2210/1281 ,  G10K2210/3026

Abstract: The inventive method for reducing the noise level of an aviation engine consists in receiving and converting a noise acoustic signal into an electric signal, transmitting the received signal to the place of the processing thereof, processing the electric signal in order to actively reduce the noise level, amplifying said signal, converting it into an acoustic signal and in emitting it to a point of space where the acoustic signals are received. The electric signals used for the active noise reduction are formed in a low-frequency region of a noise spectrum in order to increase the dimensions of a space region where noises are reduced. The inventive systems for carrying out said method are disposed in the regions of a more probable location of people which can be disturbed by the noise of aviation engines arranged inside an aircraft or thereoutside.

Abstract translation: 用于降低航空发动机的噪声水平的本发明的方法在于将噪声声信号接收并转换成电信号，将接收到的信号发送到其处理的位置，处理电信号以主动降低噪声电平 放大所述信号，将其转换成声信号并将其发射到接收声信号的空间点。 用于有源噪声降低的电信号形成在噪声频谱的低频区域中，以增加噪声减小的空间区域的尺寸。 用于执行所述方法的本发明的系统被布置在可能受到布置在飞行器内或其外侧的航空发动机的噪声扰动的人的更可能位置的区域中。

公开(公告)号：WO1998016916A1

公开(公告)日：1998-04-23

申请号：PCT/US1997012010

申请日：1997-07-10

Applicant: LORD CORPORATION

Inventor： LORD CORPORATION ,  JOLLY, Mark, R. ,  ROSSETTI, Dino, J. ,  NORRIS, Mark, A. ,  MILLER, Lane, R.

IPC: G10K11/178

CPC classification number: F16F7/1011 ,  B60G2202/25 ,  B64C2027/005 ,  B64C2220/00 ,  G10K11/17857 ,  G10K11/17861 ,  G10K11/17883 ,  G10K2210/106 ,  G10K2210/1281 ,  G10K2210/1291 ,  G10K2210/3026 ,  G10K2210/3027 ,  G10K2210/3224 ,  G10K2210/509

Abstract: A hybrid active-passive system (20) for reducing noise within a passenger compartment and vibration of a fuselage of a vehicle, such as an aircraft (turboprop, turbofan, or helicopter). The hybrid active-passive system (20) includes, in combination: an active acoustic producer such as a loudspeaker (35), Active Vibration Absorber (AVA) (34), or active absorber assembly (39) for producing antinoise within the compartment (42), and a passive resonant device, such as a passive Tuned Vibration Absorber (TVA) (36), or passive TVA assembly (37) for controlling vibration of the fuselage or structural supports interconnecting the disturbance source (e.g. power plants (26), propellers (28a), gearbox (57), main rotor (28m), tail rotor (28t)) and the fuselage wall (25).

Abstract translation: 一种用于减少乘客舱内的噪音并且诸如飞机（涡轮螺旋桨飞机，涡轮风扇或直升机）的车辆的机身的振动的混合主动 - 被动系统（20）。 混合主动被动系统（20）包括：主动声产生器，例如扬声器（35），主动减振器（AVA）（34）或主动吸收器组件（39），用于在隔室内产生防噪声 42），以及无源谐振装置，例如被动调谐振动吸收器（TVA）（36）或无源TVA组件（37），用于控制机身或互连干扰源的结构支架的振动（例如发电厂（26） ，推进器（28a），变速箱（57），主转子（28m），尾部转子（28t））和机身壁（25）。

公开(公告)号：WO1997035300A1

公开(公告)日：1997-09-25

申请号：PCT/GB1997000624

申请日：1997-03-10

Applicant: THE SECRETARY OF STATE FOR DEFENCE IN HER BRITANNIC MAJESTY'S GOVERNMENT OF THE UNITED KINGDOM OF GREAT BRITAIN AND NORTHERN IRELAND ,  JOSEPH, Philip ,  NELSON, Philip, Arthur ,  FISHER, Michael, John

Inventor： THE SECRETARY OF STATE FOR DEFENCE IN HER BRITANNIC MAJESTY'S GOVERNMENT OF THE UNITED KINGDOM OF GREAT BRITAIN AND NORTHERN IRELAND

IPC: G10K11/178

CPC classification number: G10K11/178 ,  G10K2210/111 ,  G10K2210/112 ,  G10K2210/119 ,  G10K2210/1281 ,  G10K2210/3051 ,  G10K2210/507

Abstract: A method for the active control of sound radiated in a duct (1) comprising sensing sound from an array (4) of sensors located on the inside surface of a flow duct and controlling an array (3) of secondary sources (loudspeakers) so as to minimize sound radiated in the far field. This is done by controlling the sound sources so as to minimize a cost function. Depending on whether total sound power or sound power towards the sideline is to be reduced, different cost functions are used by the method.

Abstract translation: 一种用于主动控制在管道（1）中辐射的声音的方法，包括从位于流动管道的内表面上的传感器阵列（4）感测声音并且控制次级源（扬声器）阵列（3），以便 以最小化在远场辐射的声音。 这是通过控制声源来实现的，以便最小化成本函数。 取决于是否减少总声功率或声功率，该方法使用不同的成本函数。

公开(公告)号：WO1997008683A1

公开(公告)日：1997-03-06

申请号：PCT/US1996013306

申请日：1996-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FINN, Alan, M.

IPC: G10K11/178

CPC classification number: G10K11/17857 ,  G10K11/17881 ,  G10K2210/106 ,  G10K2210/111 ,  G10K2210/12 ,  G10K2210/1281 ,  G10K2210/1282 ,  G10K2210/3027 ,  G10K2210/3215 ,  G10K2210/3219

Abstract: An active noise control system is provided with a plurality of error sensor arrays (50, 77) which provide signals on lines (64-74, 90-100) to beam forming and beam steering logic (76) which cause the arrays (50, 77) to exhibit acoustic response profiles (104, 106), respectively. The profiles (104, 106) intersect in a predefined region (116) to be quieted. The logic (76) provides signals on lines (118), one for each region to be quieted, to active noise control (ANC) logic (20) which also receives inputs from feedforward sensing microphones (10) and provides output signals to acoustic speakers (24) which generate anti-noise (26) to cancel the noise in the quiet region (116). The quiet region (116) may be selectively positioned to any region in the room by steering the beams (104, 108). Alternatively, the system may have a plurality of distributed sensors which, when taken together, have an overall maximum (main lobe) acoustic response at a predetermined selectable quiet region.

Abstract translation: 主动噪声控制系统设置有多个误差传感器阵列（50,77），它们将线路（64-74,90-100）上的信号提供给波束成形和波束控制逻辑（76），这导致阵列（50， 77）分别显示声响应曲线（104,106）。 轮廓（104,106）在预定义的区域（116）中相交以被安静。 逻辑（76）在线路（118）上提供信号，一个用于要安静的每个区域，用于还接收来自前馈感测麦克风（10）的输入的有源噪声控制（ANC）逻辑（20），并向声学扬声器提供输出信号 （24），其产生抗噪声（26）以消除安静区域（116）中的噪声。 安静区域（116）可以通过转向梁（104,108）而被选择性地定位到房间中的任何区域。 或者，系统可以具有多个分布式传感器，当它们一起在预定的可选安静区域具有总体最大（主瓣）声响应时。

公开(公告)号：WO1996012269A1

公开(公告)日：1996-04-25

申请号：PCT/US1995012725

申请日：1995-10-12

Applicant: THE BOEING COMPANY

Inventor： THE BOEING COMPANY ,  OLSEN, Ronald, F. ,  ORZECHOWSKI, Jeffery, M.

IPC: G10K11/178

CPC classification number: G10K11/178 ,  F05B2260/962 ,  G10K2210/109 ,  G10K2210/112 ,  G10K2210/121 ,  G10K2210/1281 ,  G10K2210/3026 ,  G10K2210/3027 ,  G10K2210/3045 ,  G10K2210/3046 ,  G10K2210/32121 ,  G10K2210/3229

Abstract: A jet engine fan noise reduction system. The noise reduction system includes active noise control to suppress fan (15) tone noise of an airplane flyover noise signature. The active noise control includes microphones (1, 11) with acoustic transducers upstream and downstream of the engine fan (15) and fan exit guide vane (16) stage to sense control system errors. Control signals are derived from the fan angular speed or blade passing frequency and the error signal sensed by the acoustic transducers. The control output signals actuate (modulate) air control valves (45) on each side of the fan stage to direct conditioned (pressure and temperature regulated) high pressure primary air flow, thereby producing acoustic cancelling of fan tone noise.

Abstract translation: 喷气发动机风扇降噪系统。 噪声降低系统包括主动噪声控制以抑制飞机飞越噪声特征的风扇（15）音噪声。 主动噪声控制包括具有在发动机风扇（15）上游和下游的声学换能器和风扇出口导叶（16）级的麦克风（1,11），用于感测控制系统误差。 控制信号来自风扇角速度或叶片通过频率以及由声换能器感测到的误差信号。 控制输出信号驱动（调制）风扇台两侧的空气控制阀（45），以引导调节（压力和温度调节）高压一次空气流，从而产生声音消除风扇噪音。

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：WO87007974A1

公开(公告)日：1987-12-30

申请号：PCT/GB1987000442

申请日：1987-12-30

IPC: B64C1/40 ,  B64C11/50 ,  F01N1/00 ,  G10K11/178 ,  H04R3/00 ,  G10K11/16

CPC classification number: B64C1/40 ,  B64C11/50 ,  G10K11/178 ,  G10K2210/123 ,  G10K2210/1281 ,  G10K2210/3046

Abstract: In propeller of fan driven aircraft, cabin noise levels may be reduced by adjustment of the phase relationship between a reference propeller or fan and some or all of the other propellers or fans. An aircraft cabin (1) contains four microphones (2, 3, 4, 5) and two loudspeakers (6, 7) which form the active elements of a noise control system. The microphone outputs are fed via amplifiers (12, 13, 14, 15) to a digital signal processor (11) having an adaptation algorithm in a memory store. The processor generates an error signal which is used to adjust the synchrophase angle between the reference propeller (10) and a synchrophased propeller (9), controlled by a synchrophaser (8). Thus the synchrophase angle is varied dynamically during flight to minimise propeller noise in the cabin over a range of flying condiditons.

Abstract translation: 在风扇驱动飞机的螺旋桨中，通过调整参考螺旋桨或风扇与部分或全部其他螺旋桨或风扇之间的相位关系，可能会降低舱室噪音水平。 飞机机舱（1）包含四个麦克风（2,3,4,5）和两个形成噪声控制系统的有源元件的扬声器（6,7）。 麦克风输出通过放大器（12,13,14,15）馈送到在存储器存储器中具有适配算法的数字信号处理器（11）。 处理器产生误差信号，该误差信号用于调节参考螺旋桨（10）和由同步激光器（8）控制的同步螺旋桨（9）之间的同步相位角。 因此，在飞行期间，同步酶角度被动态地变化，以使飞机上的舱室范围内的螺旋桨噪声最小化。

公开(公告)号：WO1981000638A1

公开(公告)日：1981-03-05

申请号：PCT/GB1980000128

申请日：1980-08-15

Applicant: SOUND ATTENUATORS LTD ,  POWELL A ,  CHAPLIN G ,  SMITH R

Inventor： SOUND ATTENUATORS LTD

IPC: G10K11/16

CPC classification number: F01N1/065 ,  F02B1/04 ,  F16F15/02 ,  G10K11/178 ,  G10K2210/128 ,  G10K2210/1281 ,  G10K2210/3012 ,  G10K2210/3045 ,  G10K2210/3053

Abstract: A method of reducing the adaption time needed to adapt a synthetically generated secondary waveform so that it nulls a primary repetitive waveform (e.g. noise) from a source (1) of vibration, the secondary waveform generation (5) being synchronised by the source (1). The polarity and/or the amplitude of at least a part of the signal resulting from interaction between the primary and secondary waveforms is sensed (6) and used (7, 8) to reshape the secondary waveform. The invention finds application in the cancelling of repetitive vibrations (e.g. in quietening the driving cab of a vehicle).

Abstract translation: 一种减少适应合成产生的次级波形所需的适应时间的方法，使得其消除来自振动源（1）的主要重复波形（例如噪声），次级波形产生（5）由源（1）同步 ）。 感测（6）并使用（7,8）来重新形成次级波形的由主波和辅波形之间的相互作用产生的信号的至少一部分的极性和/或振幅。 本发明可以应用于消除重复振动（例如在使车辆的驾驶室变平静）。

公开(公告)号：WO2017048464A1

公开(公告)日：2017-03-23

申请号：PCT/US2016/048095

申请日：2016-08-22

Applicant: AMAZON TECHNOLOGIES, INC.

Inventor： BECKMAN, Brian C. ,  KIMCHI, Gur

IPC: G10K11/178 ,  B64C39/02 ,  G05D19/02 ,  G05D27/02 ,  G05D1/10

CPC classification number: G10K11/178 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2220/00 ,  G01S19/13 ,  G05D1/101 ,  G05D19/02 ,  G05D27/02 ,  G06N99/005 ,  G10K11/17823 ,  G10K11/17853 ,  G10K11/17873 ,  G10K2210/1281 ,  G10K2210/30231 ,  G10K2210/30351 ,  G10K2210/3038 ,  G10K2210/3045

Abstract: Noises that are to be emitted by an aerial vehicle (1210) during operations may be predicted using one or more machine learning systems, algorithms or techniques. Anti-noises having equal or similar intensities and equal but out-of-phase frequencies may be identified and generated based on the predicted noises, thereby reducing or eliminating the net effect of the noises. The machine learning systems, algorithms or techniques used to predict such noises may be trained using emitted sound pressure levels observed during prior operations of aerial vehicles, as well as environmental conditions, operational characteristics of the aerial vehicles or locations of the aerial vehicles during such prior operations. Anti-noises may be identified and generated based on an overall sound profile of the aerial vehicle, or on individual sounds emitted by the aerial vehicle by discrete sources.

Abstract translation: 可以使用一个或多个机器学习系统，算法或技术来预测在操作期间由飞行器（1210）发射的噪声。 可以基于预测的噪声来识别和产生具有相同或相似的强度和等于或相同的频率的抗噪声，从而减少或消除噪声的净效应。 可以使用用于预测这种噪声的机器学习系统，算法或技术来使用在先前的飞行器操作期间观察到的发射声压级，以及环境条件，空中飞行器的操作特性或在这样的前述过程中的空中飞行器的位置 操作。 可以基于飞行器的整体声音轮廓或由离散源的飞行器发出的单独声音来识别和产生抗噪声。