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61. 发明申请

US20020128072A1 Active system and method for vibration and noise reduction 失效
标题翻译：主动减振系统及方法
公开(公告)号：US20020128072A1
公开(公告)日：2002-09-12
申请号：US09952412
申请日：2001-09-14
发明人： Gregory Weston Terpay , George G. Zipfel , William Welsh
IPC分类号： F16D003/10
CPC分类号： B64C27/001 , B64C2220/00 , F16F15/027
摘要： An active mount is provided for use in a rotary wing aircraft between each of the gearbox and airframe mounting locations for mechanically suspending the airframe from the gearbox. The active mount comprises first and second linear hydraulic actuators each having a principal axis. The length of the actuators is variable along the principal axis for providing relative movement between the airframe and the gearbox. The principal axes of the actuators are adapted to lie in the directional planes of the primary forces necessary for supporting the airframe and acting on the transmission gearbox mounting locations for providing movement of the gearbox relative to the airframe in the planes at a frequency for reducing the transfer of vibration through the active mount to the airframe. A system for reducing vibration in the rotary wing aircraft further comprises a hydraulic system for supplying a controlled flow of pressurized hydraulic fluid to the actuators.
摘要翻译：提供了一种用于在每个齿轮箱和机身安装位置之间的旋转翼飞行器中的主动安装座，用于机械地将机身悬挂在变速箱上。主动安装件包括每个具有主轴线的第一和第二线性液压致动器。致动器的长度沿着主轴线是可变的，用于提供机身和齿轮箱之间的相对运动。致动器的主轴适于位于支撑机身并作用在传动齿轮箱安装位置上所需的主要力的方向平面中，以提供齿轮箱相对于平面中的机身的运动，频率为减少通过主动安装座将振动传递到机身。用于减少旋转翼飞行器中的振动的系统还包括用于向致动器提供受控流动的加压液压流体的液压系统。

62. 发明授权

US06402089B1 System for control of active system for vibration and noise reduction 失效
公开(公告)号：US06402089B1
公开(公告)日：2002-06-11
申请号：US09798420
申请日：2001-03-02
申请人： John C. Kiss , Michael H. Silverberg
发明人： John C. Kiss , Michael H. Silverberg
IPC分类号： B64C2751
CPC分类号： B64C27/001 , B64C2220/00
摘要： An adaptive controller is used to adaptively generate vibration cancellation signals driving a controlled device which effects an associated vibration and noise-producing plant. The adaptive controller has multiple control paths to generate the control signal. In a vibration attenuation control path(s), an adaptive control signal is generated by plant compensation and adaptive filtering techniques to cancel vibrations. In a position control, saturation prevention path, the available operational extents of the controlled device are monitored and compensation signals are generated which direct the movement of the controlled device in such a manner as to prevent the controlled device from reaching the extents of control. The control signals from the multiple paths are then combined and transmitted to the controlled device which alters in some fashion the noise and vibration being generated or transmitted by the associated vibrating plant.

63. 发明授权

US06394397B1 Lifting surface with active variable tip member and method for influencing lifting surface behavior therewith 有权
标题翻译：具有活动可变尖端构件的提升表面和用于影响提升表面行为的方法
公开(公告)号：US06394397B1
公开(公告)日：2002-05-28
申请号：US09730702
申请日：2000-12-06
申请人： Hieu T. Ngo , Lisa E. Barlow
发明人： Hieu T. Ngo , Lisa E. Barlow
IPC分类号： B64C2300
CPC分类号： B64C27/463 , B64C23/072 , B64C2220/00 , Y02T50/164
摘要： A tip member is movable mount at the outboard end of a main lifting member such as a wing or rotor blade. The main lifting member at least at the outboard end has an internal cavity defined therein between pressure-side and suction-side surfaces of the main lifting member. The tip member is movable relative to the main lifting member between a neutral position in which the tip member presents substantially no obstacle to a spanwise component of flow over either suction-side or pressure-side surfaces at the outboard end of the main lifting member, and a position in which a portion of the tip member extends beyond on of the pressure-side and suction-side surfaces of the main lifting member so as to present an obstacle to the spanwise component of flow over that surface at the outboard end of the main lifting member and thereby locally affect the flow at the outboard end. An actuation system for the tip member is disposed in the cavity of the main lifting member and coupled with the tip member for moving the tip member so as to vary a distance by which the tip member extends beyond the surface of the main lifting member. The tip member can be placed in stationary positions, or can be cyclically moved for achieving various effects such a vibration abatement, noise suppression, or lift augmentation.
摘要翻译：尖端构件可移动地安装在诸如机翼或转子叶片的主提升构件的外侧。至少在外侧端部的主提升构件具有限定在主提升构件的压力侧和吸力侧表面之间的内部空腔。顶端构件可在中间位置之间相对于主提升构件移动，其中尖端构件在主提升构件的外侧端部的任一吸入侧或压力侧表面上基本上没有阻碍跨越翼展方向的分量，以及其中顶端部件的一部分延伸超过主提升部件的压力侧和吸入侧表面的位置，以便在该外表面上的该表面上的横向分量的障碍物主提升构件，从而局部地影响外侧的流动。用于尖端构件的致动系统设置在主提升构件的空腔中并与尖端构件联接以用于移动尖端构件，以便改变尖端构件延伸超过主提升构件的表面的距离。尖端构件可以放置在静止位置，或者可以循环地移动，以实现减震，噪声抑制或提升增加等各种效果。

64. 发明授权

US4922096A System for monitoring and controlling physical movement 失效
标题翻译：用于监测和控制身体运动的系统
公开(公告)号：US4922096A
公开(公告)日：1990-05-01
申请号：US320668
申请日：1989-03-08
申请人： Brian W. Brennan
发明人： Brian W. Brennan
IPC分类号： H02N2/00 , B64C3/48 , B64C27/00 , H01L41/04
CPC分类号： H01L41/042 , B64C27/001 , B64C3/48 , B64C2220/00
摘要： The method of the invention provides for actuating at least one actuator, such as a piezoelectric transducer in response to movement of a waveguide, such as an optical fiber. In a preferred embodiment of the invention, both the piezoelectric member and the optical fiber are connected to a structure. The connection is such that movement of the structure is detected by corresponding variations in and/or back scattering from light transmitted into the optical fiber. The piezoelectric member is actuated in response to the movement of the structural member as detected by the variations in the light in passing through the optical fiber. The actuation of the piezoelectric member may effect a dampening of the initial structural movement. Alternatively, monitoring the light passing through the fiber may be used as feed back on the position of the structural member, which in turn may be used to reposition the structural member by further actuation of a piezoelectric member.
摘要翻译：本发明的方法提供了响应于波导（例如光纤）的运动来致动至少一个致动器，例如压电换能器。在本发明的优选实施例中，压电元件和光纤都连接到结构上。这种连接使得结构的移动通过从传输到光纤中的光的相应变化和/或反向散射来检测。响应于通过光纤中的光的变化所检测到的结构构件的运动，致动压电构件。压电元件的致动可能会影响初始结构运动的衰减。或者，监视通过光纤的光可以用作反馈到结构部件的位置，反过来又可以用于通过进一步致动压电部件来重新定位结构部件。

65. 发明授权

US12057021B2 Dynamic aircraft routing 有权
公开(公告)号：US12057021B2
公开(公告)日：2024-08-06
申请号：US17570071
申请日：2022-01-06
申请人： Joby Aero, Inc.
发明人： Lan Andreas Villa , Thomas Prevot , John Conway Badalamenti , Mark Moore
IPC分类号： G01C23/00 , B64C29/00 , G01C21/20 , G01C21/34 , G05D1/00 , G06Q10/047 , G06Q10/0631 , G08G5/00
CPC分类号： G08G5/003 , B64C29/00 , B64C29/0016 , G01C21/20 , G01C21/3461 , G05D1/0202 , G06Q10/047 , G06Q10/06315 , G08G5/0013 , G08G5/0034 , G08G5/0039 , G08G5/0043 , B64C29/0025 , B64C29/0033 , B64C2220/00 , G05D1/102 , G10K2210/1281 , G10K2210/3016 , G10K2210/30231
摘要： A request for transport services that identifies a rider, an origin, and a destination is received from a client device. Eligibility of the request to be serviced by a vertical take-off and landing (VTOL) aircraft is determined based on the origin and the destination. A transportation system determines a first and a second hub for a leg of the transport request serviced by the VTOL aircraft and calculates a set of candidate routes from the first hub to the second hub. A provisioned route is selected from among the set of candidate routes based on network and environmental parameters and objectives including pre-determined acceptable noise levels, weather, and the presence and planned routes of other VTOL aircrafts along each of the candidate routes.

66. 发明授权

US12049313B2 Vibration-damped aircraft wheel bin 有权
公开(公告)号：US12049313B2
公开(公告)日：2024-07-30
申请号：US18072819
申请日：2022-12-01
申请人： AIRBUS CANADA MANAGING GP INC.
发明人： Abdolreza Madjlesi , Thineshan Kathirchelvan
IPC分类号： B64C7/00 , B64C1/40 , B64C25/00 , G10K11/172
CPC分类号： B64C7/00 , B64C1/40 , B64C25/001 , G10K11/172 , B64C2025/003 , B64C2220/00
摘要： An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

67. 发明公开

US20240182152A1 NOISE REDUCING NOSECONE FOR AIRCRAFT 审中-公开
公开(公告)号：US20240182152A1
公开(公告)日：2024-06-06
申请号：US18285402
申请日：2022-04-28
申请人： ZIPLINE INTERNATIONAL INC.
发明人： Brendan Doyle Wade , Philip M. Green
IPC分类号： B64C1/06 , B64C1/00 , H04R1/02 , H04R1/04 , H04R1/08 , H04R1/28
CPC分类号： B64C1/0683 , H04R1/028 , H04R1/04 , H04R1/086 , H04R1/2876 , B64C2001/0054 , B64C2220/00 , H04R2410/07 , H04R2499/13
摘要： A nosecone of an aircraft sensor probe may include a first portion defining a tip of the nosecone that is formed from a first material. The nosecone further includes a second portion aft of the first portion and formed from a second material. The second portion may define an internal volume. The second material may have a greater porosity than the first material. The nosecone may further include a third portion aft of the second portion. The third portion may be configured to arrange a microphone assembly relative to the internal volume. The nosecone may a component or subassembly or a sensor probe for the aircraft. For example, the sensor probe may include the nosecone and the microphone assembly. The nosecone may be configured to block the audio signals at the tip and reduce turbulent noise of the audio signals associated with non-parallel local flow angles of the airflow.

68. 发明授权

US11990113B2 Drone noise cancellation using sound beams 有权
公开(公告)号：US11990113B2
公开(公告)日：2024-05-21
申请号：US17659682
申请日：2022-04-19
申请人： UAVPatent Corp.
发明人： George Michael Matus , Shawn Ray Nageli
IPC分类号： G10K11/178 , B64C39/02 , B64D7/08 , B64D47/08 , B64U10/13 , G05D1/00 , G06T7/70 , G06V20/17 , G10L21/0216 , G10L21/0232 , G10L25/18 , G10L25/51 , H04R1/32 , H04R1/40 , H04R3/00 , B64U101/30
CPC分类号： G10K11/17827 , B64C39/024 , B64D47/08 , G05D1/0094 , G05D1/12 , G06T7/70 , G06V20/17 , G10K11/17823 , G10K11/17854 , G10K11/17873 , G10L21/0232 , G10L25/18 , G10L25/51 , H04R1/323 , H04R1/406 , H04R3/005 , B64C2220/00 , B64U10/13 , B64U2101/30 , G06T2207/10032 , G06V2201/07 , G10K2200/10 , G10K2210/1281 , G10K2210/3027 , G10K2210/3028 , G10L2021/02166
摘要： A drone includes a motor, a noise receiver, a camera, a distance measurer, and a directed sound beam generator. The noise receiver is configured to detect a noise caused by the motor. The camera is configured to capture an image of an area when the drone is in the air. The distance measurer is configured to measure a distance between the drone and a particular point in the captured image. The directed sound beam generator is configured to emit a sound beam that is directed to a particular direction. The drone further includes a processor configured to analyze the detected noise to determine a frequency spectrum of the detected noise. The processor is further configured to analyze the captured image to identify a target, and cause the directed sound beam generator to emit a sound beam to actively cancel at least a portion of the noise directed to the target.

69. 发明公开

US20240002039A1 PASSIVE VIBRATION DAMPING DEVICE FOR AIRCRAFT 审中-公开
公开(公告)号：US20240002039A1
公开(公告)日：2024-01-04
申请号：US17918703
申请日：2022-01-24
申请人： LEONARDO S.P.A.
发明人： Nicola GRAVAGNONE , Massimiliano DI GIULIO
IPC分类号： B64C11/04 , F16F7/108
CPC分类号： B64C11/04 , F16F7/108 , B64C2220/00
摘要： A passive multi-frequency damping device for damping vibrations of an aircraft has a support structure, a plurality of N metal damping masses, each having a respective n-th mass, N being a natural number greater than or equal to 2, and n being a natural number from 1 to N, a plurality of N elastic elements each having a respective n-th stiffness, and each being glued to both the support structure and a respective n-th damping mass to support the respective n-th damping mass on the support structure so that the respective n-th damping mass is free to vibrate relative to the support structure. For each n from 2 to N, each n-th damping mass is arranged to at least partially surround an n−1-th damping mass. The first damping mass has a solid semi-cylindrical shape, and the remaining damping masses have a hollow semi-cylindrical shape.

70. 发明公开

US20230377551A1 ELECTRONIC NOISE CANCELLATION TECHNIQUES FOR AIRCRAFT ENCLOSURES AND/OR OTHER ENCLOSURES 审中-公开
公开(公告)号：US20230377551A1
公开(公告)日：2023-11-23
申请号：US18195051
申请日：2023-05-09
申请人： INNOVATIVE SOLUTIONS & SUPPORT, INC.
发明人： Shahram Askarpour
IPC分类号： G10K11/178 , F21V33/00 , B64C11/00
CPC分类号： G10K11/17823 , G10K11/17873 , F21V33/0056 , B64C11/00 , G10K2210/3044 , G10K2210/3046 , G10K2210/3027 , G10K2210/1281 , G10K2210/504 , B64C2220/00
摘要： This disclosure relates to improved techniques for electronic noise cancellation in aircraft and other enclosures. In certain embodiments, an electronic noise cancellation device can be installed in an aircraft. In certain embodiments, the electronic noise cancellation device can include a housing that integrates: one or more audio input devices that are configured to receive an input audio signal; one or more audio output devices configured to output a noise cancellation signal; one or more lighting components; and at least one connector that enables the electronic noise cancellation device to be coupled to an overhead service component of the aircraft. In certain embodiments, the electronic noise cancellation device is adapted to be received in a lighting socket of the overhead service component included within an aircraft enclosure. Other embodiments are disclosed.

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