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1. 发明申请

WO2011163316A3 METHOD AND SYSTEM FOR DETECTING PUSHROD FAULTS 审中-公开
标题翻译：检测按键故障的方法和系统
公开(公告)号：WO2011163316A3
公开(公告)日：2012-04-19
申请号：PCT/US2011041374
申请日：2011-06-22
申请人： SIKORSKY AIRCRAFT CORP , ISOM JOSHUA D , DAVIS MARK W , WELSH WILLIAM A , MORRIS BRIAN EDWARD , CYCON JAMES PETER
发明人： ISOM JOSHUA D , DAVIS MARK W , WELSH WILLIAM A , MORRIS BRIAN EDWARD , CYCON JAMES PETER
IPC分类号： B64D45/00 , B64C13/18 , B64C27/32 , B64F1/22
CPC分类号： B64D45/00 , B64D2045/0085 , B64F5/60 , G05B23/0243
摘要： A system for monitoring for pushrod faults in an aircraft includes a pushrod; a sensor (36) mounted on the pushrod (34), the sensor (36) wirelessly transmitting measured pushrod load data; a receiver (44) receiving the measured pushrod load data; a model (42) receiving flight data and generating a modeled pushrod load profile; and a fault detector (46) comparing measured pushrod load data to the modeled pushrod load profile to detect a pushrod fault.
摘要翻译：用于监视飞机中的推杆故障的系统包括推杆; 安装在推杆（34）上的传感器（36），所述传感器（36）无线地传送测量的推送负载数据; 接收器（44），接收测量的推送负载数据; 接收飞行数据并生成建模的推送负载曲线的模型（42）; 以及故障检测器（46）将测量的推送负载数据与建模的推送负载分布进行比较以检测推杆故障。

2. 发明申请

WO2008033884A3 DUAL HIGHER HARMONIC CONTROL (HHC) FOR A COUNTER-ROTATING, COAXIAL ROTOR SYSTEM 审中-公开
标题翻译：用于反转同轴转子系统的双重高谐波控制（HHC）
公开(公告)号：WO2008033884A3
公开(公告)日：2008-06-19
申请号：PCT/US2007078222
申请日：2007-09-12
申请人： SIKORSKY AIRCRAFT CORP , WELSH WILLIAM A
发明人： WELSH WILLIAM A
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C27/10 , B64C2027/7233 , B64C2027/7238 , Y02T50/34
摘要： A higher harmonic control (HHC) system individually controls an upper HHC actuator system, and a lower HHC system to minimize vibration.
摘要翻译：高次谐波控制（HHC）系统可分别控制上部HHC执行器系统和下部HHC系统以最小化振动。

3. 发明申请

WO2005079200A3 ACTIVE FORCE GENERATION SYSTEM FOR MINIMIZING VIBRATION IN A ROTATING SYSTEM 审中-公开
标题翻译：用于最小化旋转系统中的振动的主动力生成系统
公开(公告)号：WO2005079200A3
公开(公告)日：2007-12-21
申请号：PCT/US2004033842
申请日：2004-10-13
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A
IPC分类号： F16C15/00 , B64C27/00 , F16F15/14 , F16F15/36
CPC分类号： F16F15/145 , B64C27/001 , B64C2027/004 , F16F15/36 , Y10S416/50
摘要： A method and device for reducing vibratory noise in a system with an integral rotating member includes independently operable drive means for controlling the angular velocity of at least two masses. Control signals manipulate the drive means to allow each mass to rotate at optimal speed, direction and phase for reducing the noise induced in the system by the rotating member.
摘要翻译：一种用于减小具有整体旋转构件的系统中的振动噪声的方法和装置包括用于控制至少两个质量的角速度的独立可操作的驱动装置。控制信号操纵驱动装置以允许每个质量块以最佳速度，方向和相位旋转，以减少由旋转构件在系统中引起的噪声。

4. 发明申请

WO9910877A3 ACTIVE NOISE CONTROL SYSTEM FOR A DEFINED VOLUME 审中-公开
标题翻译：用于定义体积的主动式噪声控制系统
公开(公告)号：WO9910877A3
公开(公告)日：1999-06-03
申请号：PCT/US9817121
申请日：1998-08-18
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A , YOERKIE CHARLES A JR
IPC分类号： B64C27/04 , F16F15/02 , G10K11/178 , B64C27/00
CPC分类号： G10K11/178 , G10K2210/106 , G10K2210/1281 , G10K2210/1282 , G10K2210/1291 , G10K2210/3027 , G10K2210/501 , G10K2210/511
摘要： An active noise control system (12) for minimizing undesirable acoustic noise in a defined volume, wherein the undesirable acoustic noise is generated by high frequency structural vibrations emanating from a vibration source structurally coupled to the defined volume at a structural interface. The active noise control system (12) comprises a sensor subsystem (26) disposed in combination with the defined volume (14) for sensing the undesirable acoustic noise in the defined volume (14), an actuator subsystem (28) disposed proximal to the structural interface (22), and a controller (30) functionally interconnecting the sensor subsystem (26) to the actuator subsystem (28), the controller (30) being operative to receive input from the sensor subsystem (26) and to transmit command signals to the actuator subsystem (28) in response thereto for generating selected high frequency counter-vibrations that are interactive with the high frequency structural vibrations to minimize the undesirable acoustic noise in the defined volume (14).
摘要翻译：一种有源噪声控制系统（12），用于最小化限定体积内的不合需要的噪声，其中不希望的噪声是由结构性耦合到结构界面处的限定体积的振动源发出的高频结构振动产生的。主动噪声控制系统（12）包括与限定体积（14）组合布置的传感器子系统（26），用于感测限定体积（14）中的不希望的噪声;致动器子系统（28），布置在结构接口（22）以及将传感器子系统（26）功能性地互连到致动器子系统（28）的控制器（30），控制器（30）可操作以接收来自传感器子系统（26）的输入并将命令信号致动器子系统（28）响应于此而产生与高频结构振动相互作用的选定的高频反振动，以最小化限定体积（14）中的不希望的噪声。

5. 发明申请

WO2005111460A3 MAGNETORHEOLOGICAL (MRF) ACTIVE ISOLATION SYSTEM 审中-公开
标题翻译：磁共振（MRF）主动隔离系统
公开(公告)号：WO2005111460A3
公开(公告)日：2006-12-28
申请号：PCT/US2004034027
申请日：2004-10-13
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A , TOROK MICHAEL S
IPC分类号： F16F15/03 , F03D5/06 , F16F15/36
CPC分类号： F16F15/366 , F16F2224/045 , Y10S416/50
摘要： A system for reducing vibrations in a rotating system uses a variable viscosity medium (26) that is redistributed in a housing (20) connected to the rotating system (2). Specifically, the medium is responsive to a control signal that is generated as a function of rotational speed of the rotational system. The control signal activates a triggering device that promotes a change in viscosity of the medium such that it is distributed within the housing in a manner that reduces vibratory loads.
摘要翻译：用于减少旋转系统中的振动的系统使用重新分布在连接到旋转系统（2）的壳体（20）中的可变粘度介质（26）。具体地，介质响应于作为旋转系统的转速的函数而产生的控制信号。控制信号激活触发装置，其促进介质粘度的变化，使得其以减少振动载荷的方式分布在壳体内。

6. 发明申请

WO2016053859A3 HUB SEPARATION IN DUAL ROTOR ROTARY WING AIRCRAFT 审中-公开
标题翻译：双转子旋翼飞机的毂分离
公开(公告)号：WO2016053859A3
公开(公告)日：2016-05-26
申请号：PCT/US2015052619
申请日：2015-09-28
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A , WEINER STEVEN D , BLACKWELL JR ROBERT H , BRIGLEY MIKEL , HUNTER DAVID H
IPC分类号： B64C27/04
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C11/48 , B64C11/50 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , B64D2045/0085 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; and a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135.
摘要翻译：飞机包括机身; 延长的尾巴; 反转同轴主转子组件，其包括上转子组件和下转子组件; 以及位于所述延伸尾部处的平移推力系统，所述平移推力系统向所述机身提供平移推力; 其中（i）所述上部转子组件的所述毂和所述下部转子组件的所述毂之间的所述毂分离与（ii）所述上部转子组件的半径之比在约0.1和约0.135之间。

7. 发明专利

BR9814338A 未知
公开(公告)号：BR9814338A
公开(公告)日：2000-10-03
申请号：BR9814338
申请日：1998-12-04
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A , YOERKIE CHARLES A
IPC分类号： B64C27/12 , B64C27/00 , F16F7/10 , F16F15/00 , F16F15/02 , G10K11/178
摘要： An active noise control system for a helicopter for minimizing undesirable acoustic noise in a cabin defined by a cabin structure, wherein the undesirable acoustic noise is generated by high frequency structural vibrations emanating from a gearbox, and wherein the gearbox has a plurality of attachment feet structurally coupling the gearbox to the cabin structure at a plurality of structural interfaces. The active noise control system comprises a sensor subsystem disposed in combination with the cabin for sensing the undesirable acoustic noise in the cabin, an actuator subsystem disposed in combination with at least one of the plurality of attachment feet, and a controller functionally interconnecting the sensor subsystem to the actuator subsystem, the controller being operative to receive input from the sensor subsystem and to transmit command signals to the actuator subsystem in response thereto for generating at least one high frequency counter-vibration that is interactive with the high frequency vibrations to minimize the undesirable acoustic noise in the cabin. The active noise control system further includes at least one flange connected to the attachment feet proximal to the corresponding structural interface, and wherein the actuator subsystem further includes at least one structural actuator disposed in combination with the flange.

8. 发明专利

CA2316243A1 ACTIVE NOISE CONTROL SYSTEM FOR A HELICOPTER GEARBOX MOUNT 未知
公开(公告)号：CA2316243A1
公开(公告)日：1999-07-01
申请号：CA2316243
申请日：1998-12-04
申请人： SIKORSKY AIRCRAFT CORP
发明人： YOERKIE CHARLES A JR , WELSH WILLIAM A
IPC分类号： B64C27/12 , B64C27/00 , F16F7/10 , F16F15/00 , F16F15/02 , G10K11/178
摘要： An active noise control system (12) for a helicopter (10) for minimizing undesirable acoustic noise in a cabin (14, 15), wherein said noise is generated by high frequency structural vibrations emanating from a gearbox (16), and wherein the gearbox has a plurality of attachment feet (18) structurally coupling the gearbox to a cabin structure. The active noise control system comprises a sensor subsystem (26) disposed in combination with the cabin for sensing the said noise in the cabin, or in combination with the gearbox, an actuator subsystem (28) disposed in combination with at least one of said attachment feet, and a controller (30) functionally interconnecting the sensor subsystem to the actuator subsystem, the controller being operative to receive input from the sensor subsystem and to transmit command signals to the actuator subsystem in response thereto for generating at least one high frequency counter-vibration that is interactive with the high frequency vibrations to minimize said noise in the cabin.

9. 发明公开

EP1730029A4 GEARBOX MOUNTED FORCE GENERATOR 有权
标题翻译：传动装电源发电机
公开(公告)号：EP1730029A4
公开(公告)日：2011-09-07
申请号：EP05752219
申请日：2005-03-10
申请人： SIKORSKY AIRCRAFT CORP
发明人： WELSH WILLIAM A , ELLER EREZ , GOODMAN ROBERT K
IPC分类号： B63H1/00 , B64C27/00 , B64C27/14
CPC分类号： B64C27/14 , B64C27/001

10. 发明公开

EP3197771A4 ANTI-VIBRATION MOMENT GENERATING AIRCRAFT ACTUATION SYSTEM 有权
公开(公告)号：EP3197771A4
公开(公告)日：2018-05-30
申请号：EP15849690
申请日：2015-09-23
申请人： SIKORSKY AIRCRAFT CORP
发明人： HUNTER DAVID H , WELSH WILLIAM A , BASKIN BRYAN KENNETH , BUTLER CHRIS PAUL
IPC分类号： B64C27/00 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/51
CPC分类号： B64C27/001 , B64C27/10 , B64C27/12 , B64C2027/002 , B64C2027/004
摘要： An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.

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